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ZONAIR User`s Manual
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1. 1 2 3 4 5 6 7 8 9 10 BODY7 BID LABEL ACOORD NAXIS NRAD NOSERAD IAXIS CBAR CONT CONT ITYPE1 X1 1 YR1 ZR1 IDY1 IDZ1 CONT CONT ITYPE2 X2 CAM2 YR2 ZR2 IDY2 IDZ2 CONT CONT ITYPE2 x3 CAM3 YR3 ZR3 IDY3 IDZ3 etc BODY7 4 BODY 2 8 4 Qa 3 NO BC BC 0 0 0 0 0 0 EF 1 10 0 0 0 5 HI HI 3 2 0 103 104 Field Contents BID Identification number Integer gt 0 See Remark 1 LABEL An arbitrary character string up to 8 characters used to define the body Character ACOORD Identification number of ACOORD bulk data card specifying body center line location and orientation Integer gt 0 or Blank Default 0 See Remark 2 NAXIS Number of axial stations 1 e divisions of the body Integer 2 2 NRAD Number of circumferential points of the body Integer 2 3 See Remark 3 NOSERAD Nose radius of blunt body NOSERAD is active only if Hypersonic Aerodynamic Method is used Real 2 0 0 See Remark 4 IAXIS The index of the axial station where the blunt nose ends Integer gt 1 IAXID is active only 1f for hypersonic aerodynamic analysis See remark 4 CBAR Character String either YES or NO For CBAR YES a set of CBAR elements will be automatically generated to model the wake that is shaded from the body character See Remark 5 ITYPEi Type of input used to define the circumferential panel cuts 1 body of revolution 2 elliptical body 3 arbitra
2. ooooo REAL A RADIANS 898252 01 349551 01 077587 02 709552 02 481243 02 BNNAN L EIGE T2 224 2 eu 2 6 zi 2 6 9 oT 1 po EIGE T2 22 sb 6 2 s 6 210 SI 1 8 52 EIGE T2 Pde d NEST EIGE T2 4 1 NVECT T3 438916E 01 682208 03 536763E 01 429644E 01 281797E 02 088563E 01 013343E 01 016269E 00 736918E 01 082150E 01 465001E 01 292082E 00 746809E 01 037815E 00 304427E 00 566373E 00 0 NVECT T3 248838E 01 626384E 03 584442E 01 027624 00 131099 01 231425 01 212290E 01 302277 00 083220 00 909589 01 315537 01 153657 01 624408 00 240496 00 081899 01 356609 01 0 NVECT T3 585293E 01 092312 02 611228 01 358505 00 117747 00 920185 01 350678 01 898809 01 326068 00 829033E 01 475777 01 657666 01 903178 01 571835E 01 253393 00 218969 00 0 NVECT T3 123309E 00 318701E 02 520594E 01 440502 01 283839E 00 EIGENVALUES CYCLES 612711 00 169717 01 306583 01 312386 01 132120 01 OR NO R1 1 046505E 03 1 641355E 04 1 233849 02 1 128285E 02 2 549300E 03 1 018326E 02 1 044415E 02 1 194192 02 9 773146 03 1 032532
3. BULK DATA DESCRIPTION 4 121 MATBODY mA NAXIS 3 T 147 x IN 1 x 129 Sosslee esEese 9292 34 BR RR m ees Banc 10 MATBODY 110 FUSEL BODY 265 YES 3 20 1 050 501 1 050 502 1 050 503 1 050 504 1 050 505 1 050 506 1 050 507 1 050 508 1 050 509 1 050 510 1 050 511 1 050 512 1 050 513 1 050 514 1 050 515 1 050 516 1 050 517 1 050 518 1 050 519 1 050 520 PANLST2 501 110 201 130 129 PANLST2 502 110 202 140 139 PANLST2 503 110 203 150 149 PANLST2 504 110 204 160 159 PANLST2 505 110 205 170 169 PANLST2 506 110 206 180 179 PANLST2 507 110 207 190 189 PANLST2 508 110 208 200 199 PANLST2 509 110 209 90 89 PANLST2 510 110 210 100 99 PANLST2 511 110 211 110 109 PANLST2 512 110 212 120 119 PANLST2 513 110 213 50 49 PANLST2 514 110 214 60 59 PANLST2 515 110 215 70 69 PANLST2 516 110 216 80 79 PANLST2 517 110 217 1 5 PANLST2 518 110 218 2 6 PANLST2 519 110 219 3 7 PANLST2 520 110 220 4 8 4 122 DATA DESCRIPTION MATWAKE MATWAKE Grouping a Set of CSHEAR Panels Description Defines the label of a curved wake surface by grouping a set of CSHEAR panels Format and Example Field Contents MID Unique identification number Integer gt 0 See Remark 1 LABEL Unique character string to define the name of the curved wake surface Character Remarks 1 The MATWAKE bulk data card is referred to by the PSHEAR bulk data ca
4. Command Description Remarks AEROGEN Invokes the aerodynamic analysis Optional Controls echo printout of Bulk Data Section Optional Invokes the aerodynamic analysis on flexible aircraft by FLEXLD referring to an identification number of the FLEXLD bulk Optional data card GENBASE Generates an Aerodynamic Database Optional LABEL 2 of the subcase by character Optional SUBCASE Delimits and identifies a subcase section Required SUBTITLE E Ser subcase section by a character Optional TITLE Describes the job by a character string up to 72 characters Optional THERMAL Invokes the aeroheating analysis Optional TRIM Invokes the static aeroelastic trim analysis discipline Optional Comment statement Optional e All Case Control Commands can be written either in lower case or upper case The Case Control Section may contain many subcases SUBCASE e Within each subcase only one discipline among can be selected e TITLE and ECHO must appear before the subcase section e SUBTITLE and LABEL must appear within the subcase section Each subcase is initiated by the command 3 34 CASE CONTROL SECTION AEROGEN AEROGEN Invokes the Aerodynamic Analysis Discipline Description Invokes the aerodynamic analysis discipline by pointing to an identification number of the AEROGEN bulk data card Format AEROGEN n Example AEROGEN 100 Remarks 1 AEROGE
5. Character string represents the name of the matrix MATRIXB Used only if SYMBOL is not blank Character Remarks 1 The ALTER bulk data cards provide means to perform certain matrix operations without modifying the program source code These matrix operations are executed before the program invokes any disciplines flutter ASE trim or dynamic loads analysis Note that the ALTER bulk data card is not referred to by any other bulk data cards Its existence in the Bulk Data Section triggers the program to perform the matrix operations Multiple ALTER bulk data cards can be specified where the execution sequence of the matrix operation defined by each ALTER bulk data card is performed according to the ascending order of the entry STEP 2 The execution of these ALTER bulk data cards are performed after the computation of the engineering module that is specified by the MODULE entry is completed where MODULE FEM The Matrices exist on the run time database include those imported by DMI and DMIG bulk data cards ASSIGN FEM and ASSIGN MATRIX Executive Control Commands MODULE SPLINE execution of these ALTER bulk data card after the computation of the SPLINE module is completed The matrices exist on the run time database include the SPLINE matrix called UGTKG and those of the control surface modes and LOADMOD generated by LOADMOD bulk data card MODULE UAIC After the
6. DEFORM Stores the deformed aerodynamic model on the file for graphic display If FLEX RIGID the deformation is due to the rigid body motion of the trim variables If FLEX FLEX the deformation also includes the structural deflection TYPE ELASTIC Stores the deformed aerodynamic model on the file for graphic display The deformation includes only the structural deflection no rigid body motion BULK DATA DESCRIPTION 4 147 PLTTRIM FORM Character string Character FORM TECPLOT for generating the TECPLOT file FORM PATRAN for generating the PATRAN neutral results file FORM IDEAS for generating an I DEAS universal file FORM FEMAP for generating a FEMAP neutral file FORM ANSYS for generating an ANSYS supported neutral file FORM ABAQUS for generating an ABAQUS supported file FORM NASTRAN for generating a NASTRAN bulk data deck containing FORCE and MOMENT bulk data cards Note If TYPE FORCE only FORM NASTRAN FORM IDEAS and FORM ABAQUS are supported Default TECPLOT See Remark 3 FILENM The name of the file that stores the generated data This file name is always in the uppercase letters In case the input file name is given in the lowercase letters the program will convert it to the uppercase If the first character starts with a dollar sign the rest of the characters must be integers This integer 1s the identification
7. LEE fer ee Field Contents IDPCH Unique identification number Integer gt 0 See Remark 1 FILENM Character string specifying the name of the file that is generated by NASTRAN in the punch format If the first character of FILENM starts with a dollar sign the rest of the characters must be integers This integer is the identification number of an EXTFILE bulk data card where the filename is specified This feature allows for filenames up to 72 characters to be input Character See Remark 2 ELLST Identification number of a structural element whose modal values forces stresses strains etc are to be read from the punch file Integer gt 0 FIELD The FIELD th component of the modal values of the element is to be read from the punch file Integer gt 0 See Remark 3 LABEL Character string to define a label for describing these modal values For output this label consists of the first six characters of LABEL and the last two characters are replaced by the integer defined by FIELD For instance for LABEL ELFORCE and FIELD 2 the output label becomes ELFORC02 REMARK Not used BULK DATA DESCRIPTION 4 137 PCHFILE Remarks 1 The PCHFILE bulk data card imports the modal values of a structural parameter that can be element forces stresses strains etc from the NASTRAN punch file These modal values are used to compute the resulting
8. 515 000 0 11 4 11 4 2 5 INPUT FOR STATIC AEROELASTIC TRIM ANALYSIS TRIM MODULE 4 11 4 2 6 INPUT FOR PLOT FILE GENERATION ccccccccececececececececececscecececececececececeeeeseeeeeess 4 15 4 2 7 MISCELLANEOUS 5 EE re P RR HACER eT 4 16 4 3 BULK DATA 85 00 1 0 hehehe nene n enini nene 4 17 GUIDELINES FOR AERODYNAMIC MODELING een 5 1 5 1 AERODYNAMIC COORDINATE SYSTEM ccccccecececececececececececececececececececececececececececeeeeeceeecesecece 5 1 5 2 SURFACE DISCRETIZATION BY GRID POINTS AND PANELS eere eene 5 3 5 3 WAKE MODELING tac es ctis aate Bleu ta casts Be cates 5 5 5 4 TIP VORTEX MODELING iecit b IN e EE ENG 5 6 5 5 RBE2 FOR THE WAKE MODELING BEHIND THE WING BODY JUNCTION eren 5 8 5 6 THE THIN WING 2 5 9 5 7 SUPER INCLINED PANELS IN SUPERSONIC 5 12 5 8 MODELING OF THE REAL FLOW USING THE POTENTIAL FLOW THEORY 5 13 5 9 COMPUTATIONAL TIME AND DISK SPACE REQUIREMENT ccce enne 5 14 MODELING GUIDELINES OF SPLINE FOR FLEXIBLE LOADS 6 1 6 1 ILL CONDITIONED SPLINE MATRIX DUE TO COINCIDENT FINITE ELEMENT GRID POINT LOCATIONS ccccccececececececececececececececec
9. Identification number of a WTIFRC bulk data card to specify a set of given component forces and moments Remarks 1 The WT1AJJ bulk data card generates AIC weighting matrix WT1 such that F LWT s tw BULK DATA DESCRIPTION 4 215 WTIAJJ where F is the given set of component forces and moments 4 18 the dynamic pressure L is the component load integration matrix that is jointly generated by a set of LOADMOD bulk data cards WTI is the force correction matrix generated by the WT1AJJ bulk data card is the so called uncorrected AIC matrix directly computed by the program and W is the mode by which the given set of component forces and moments are computed or measured Note that after JW T1 is computed the corrected AIC matrix defined as 4JJ where 427 WT Is stored on the run time database to compute the flexible loads of all modes 4 216 DATA DESCRIPTION WTIFRC WT1FRC Component Loads for Force Correction Matrix Description Specifies a set of component forces and moments for generating the force correction matrix Format and Example LOADMOD DYNP RFORCE1 IFORCE1 on RFORCE2 IFORCE2 LOADMOD DYNP pos RFORCE1 I FORCE1 oA RFORCE2 IFORCE255 Field Contents IDFRC Identification number that is referred to by WTIAJJ bulk data card Integer gt 0 See Remark 1 TYPE Character string to specify the type of
10. generated by NE NASTRAN see Remark 3 ASTROS generated by ASTROS see Remark 4 IDEAS generated by I DEAS see Remark 5 ELFINI generated by ELFINI see Remark 6 FREE stored according to the input instruction described in Remark 7 If no FORM is specified in the ASSIGN FEM command MSC is used as default Note For NASTRAN type of finite element code the masses attached to the scalar points SPOINT will be ignored by ZONAIR Replacing SPOINT by GRID is recommended BOUNDARY c BOUNDARY indicates the boundary condition of the structural finite EXECUTIVE CONTROL SECTION 3 3 ASSIGN FEM element model Optional c isa character string that has 3 options SYM for symmetric boundary condition for anti symmetric boundary condition ASYM for asymmetric boundary condition If no BOUNDARY is specified SYM is used as default see Remark 8 SUPORT m L Optional input to specify the degrees of freedom of the rigid body modes of the structural finite element model m is an integer representing the component numbers of the rigid body degrees of freedom It contains any unique combination of the integer 1 through 6 with no embedded blanks where 1 2 and 3 represent the translational rigid body modes along the x y and z axes of the finite element basic coordinates respectively 4 5 and 6 are the rotation rigid body modes about the
11. EVEN these NFED reference grid points are evenly distributed along each vortex roll up line For DIVIDE COS the distribution is calculated based on the cosine function In order to determine the locations of the vorticity feeding points the locations of the starting and ending points of each vortex roll up line must be specified by the user The location of the starting point 1s determined by the average position between GRIDU and GRIDL whereas the ending points where the vortex core is located must be defined by the user using a reference grid point with identification number IDSET For ROLLUP LINE the shape of the ith vortex roll up line is a straight line For ROLLUP CIRCLE the shape is a half circle with the two ending points at the starting and ending points of the vortex roll up line ROLLUP LINE ROLLUP CIRCLE The tangential vector is the average lateral vectors of the upper and lower panels where GRIDU and GRIDL are attached 4 208 DATA DESCRIPTION WAKENET WAKENET Wake Macroelement for Description Curved Wake Surface Defines a wake macroelement to automatically generate a set of CSHEAR panels for modeling a curved wake surface Format and Example 1 2 3 4 5 6 7 8 9 10 WAKENET IDWAKE LABEL NX NY SLOPE LINE1 LINEY LINETE CONT CONT GRIDU GRID
12. XRL YRL ZRL RCH ATTR LRCHD RWAKE CANTR XTL YTL ZTL TCH ATTT LTCHD TWAKE X Y and Z location of the root chord leading edge Real Length of the root chord Real Character string either YES NOBR NO For ATTR YES the root the thick wing component is attached to is a body component Note that for ATTR NOBR no CBAR elements are generated along that surface grid points behind the root of the thick wing component Represented by CQUAD4 CTRIA3 BODY7 bulk data cards Character For ATTR NO LRCHD is the identification number of an AEFACT bulk data card used to specify the root chord divisions of the wing component in percentage of the root chord The number of values listed in AEFACT must be NCHORD and must start with 0 0 and end with 100 0 If LRCHD 0 then NCHORD evenly distributed chordwise divisions for the root is used Integer 0 For ATTR YES or LRCHD 15 the identification number of a SET1 bulk data card that lists NCHORD identification number of the surface grid points GRID bulk data card with entry PS 0 or blank Integer gt 0 Note that LRCHD also can be a character string AUTO that triggers the program to automatically search for the surface grid points along the wing body junction Character AUTO See Remark 5 Identification number of a SET1 bulk data card that lists a set of identif
13. LABEL Character string that matches one of the LABEL entries of a WAKENET or VORNET macroelement Character See Remark 2 Remarks 1 RELAXW bulk data card 15 referred to by the MACH bulk data card 2 Only those WAKENET and VORNET macroelements whose LABEL entries are referred to by the RELAXW bulk data card are subjected to wake relaxation BULK DATA DESCRIPTION 4 159 SETI SET1 Set Definition for Aerodynamic Analysis Description Defines a set of integers by a list Format and Example Alternate Form z 3 4 5 6 2 8 9 10 Field Contents SID Set identification number Integer gt 0 Gi List of integers Integer gt 0 Remarks 1 When using THRU option all intermediate quantities are assumed to exist 2 SETLis a general purpose bulk data card to define a set of integers It is referred to by many other bulk data cards to define a list of bulk data card identification numbers indices of modes aerodynamic panel divisions etc 4 160 DATA DESCRIPTION SLICE SLICE Description Slice a Closed Wing Trailing Edge Slices a closed wing trailing edge and wing tip into upper and lower surfaces and automatically adds CBAR CROD RBE2 along the edges of the surface Format and Example Field EID STARTG ENDBG DIRECTI RBE2 ENDRG DIRECT2 SPLIT Remarks Contents Unique element identification number Inte
14. 2 EXTFILE can be used to enforce the reading of file names in LOWER CASE if needed File name case sensitivity can be an issue for the UNIX operating systems In this situation EXTFILE can be used to circumvent this problem 4 84 BULK DATA DESCRIPTION FLEXLD FLEXLD Aerodynamic Analysis of Flexible Aircraft Description Computes the aerodynamic pressure coefficients forces and moments of a flexible aircraft Format and Example 1 2 3 4 5 6 7 8 9 10 IDFLEX IDAERO FORM FILENM OUTPUTA FLEXLD IDFLEX IDAERO Q FORM FILENM OUTPUT4 Remarks Field Contents Identification number that is referred to by a FLEXLD Case Control Command Integer gt 0 See Remark 1 Identification number of an AEROGEN bulk data card Integer gt 0 See Remark 2 The absolute value of Q is the dynamic pressure for computing the flexible aerodynamic loads Note that Q can be a negative value In this case the follower force effects are taken into account Real See Remark 3 Character string to define the format of the output file FILENM Character FORM TECPLOT for generating the TECPLOT file FORM PATRAN for generating the PATRAN neutral results file FORM IDEAS for generating an I DEAS universal file FORM FEMAP for generating a FEMAP neutral file FORM ANSYS for generating an ANSYS supported neutral file FORM ABAQUS for generati
15. 6 3 ENSURING CONTINUOUS STRUCTURE ACROSS TWO ADJACENT CAERO7 MACROELEMENTS One of the modeling restrictions of the CAERO7 macroelement is that it can only represent trapezoidal types of surfaces i e the inboard and outboard edges must be parallel to the x axis of the aerodynamic coordinates Therefore to model a non trapezoidal type of wing like component may require more than one CAERO7 Figure 6 3 a presents a cranked wing planform that is modeled by two CAERO7 macroelements one for the inboard region and one for the outboard region The plate type finite element model shown in Figure 6 3 b has 12 grid points denoted as grid point through grid point 12 1 2 5 3 Ey CNRC 11 4 j j oe a Aerodynamic Model b Structural Finite Element Model Figure 6 3 Spline for a Cranked Wing Planform Two SPLINE1 bulk data cards are required to spline the two CAERO7 macroelements to the structure The structural finite element model by itself is a continuous structure and should not incur any discontinuous slopes Discontinuous slopes across the two CAERO7 macroelements result if the inboard CAERO7 only refers to the finite element grid points located in the inboard region grid points 1 through 8 and the outboard CAERO7 only refers to the finite grid points located in the outboard region grid points 5 through 12 Such discontinuous slopes across the two macroelements are incorrect and will lead to incorrect aeroelastic resu
16. CORD1C Cylindrical Coordinate System Definition Form 1 Description Defines a cylindrical coordinate system by reference to three grid points These points must be defined in coordinate systems whose definition does not involve the coordinate system being defined The first point is the origin the second lies on the z axis and the third lies in the plane of the azimuthal origin Format and Example 1 2 3 4 5 6 7 8 9 10 Field Contents CID Coordinate system identification number Integer gt 0 Gi Grid point identification number can be either a surface grid or a reference grid Integer gt 0 G1 G2 63 Remarks 1 Coordinate system identification numbers on all CORDIR CORDIC CORDIS CORD2R CORD2C and CORD2S entries must be unique 2 three points G1 G2 and G3 must be noncollinear 3 location of a grid point P in the sketch in this coordinate system is given by Z where is measured in degrees BULK DATA DESCRIPTION 4 55 CORDIC 4 displacement coordinate directions at P are dependent on the location of P as shown above by u ue uz 5 Points on the z axis may not have their displacement directions defined in this coordinate system since an ambiguity results 6 One or two coordinate systems may be defined on a single entry 4 56 BULK DATA DESCRIPTION CORDIR CORDIR Rectangular Coordinate System Definition Form 1 Description Defines a r
17. Format and Example 1 2 3 4 5 6 7 8 9 10 CTRIA3 EID PID G1 G2 G3 CTRIA3 100 a 4 7 8 Field Contents EID Unique element identification number Integer gt 0 PID Identification number of a PSHELL bulk data card Integer gt 0 See Remark 2 G1 G2 Identification numbers of connected grid points GRID bulk data cards G must be the G3 surface grid points PS 0 in the GRID bulk data card Unique Integer gt 0 See Remark 3 Remarks 1 Among all CQUAD4 CTRIA3 CAERO7 and BODY7 bulk data cards EID must be unique 2 The PSHELL bulk data card must exist 3 sequence of the three corner grid points defines the out normal vector of the panel as shown below 4 G G The user must ensure the the out normal vector is toward outside the aerodynamic model Incorrect out normal vector will definitely lead to wrong results Note that the program subdivides each CTRIA3 panel into four sub triangular panels shown below BULK DATA DESCRIPTION 4 75 CTRIA3 4 76 BULK DATA DESCRIPTION DMI DMI Header of Direct Matrix Input Description Defines the header information of DMIS or DMIL bulk data cards Format and Example 1 2 3 4 5 6 Z 8 10 DMI NAME ZERO FORM TIN TOUT LARGE M DMI BBB 0 2 DMIS 7 Field Contents Name of the matrix Character See Remark 1 ZERO Mus
18. for generating a FEMAP neutral file FORM ANSYS for generating a ANSYS supported neutral file FORM NASTRAN for generating a NASTRAN bulk data deck FILEMESH Character string up to 16 characters to specify the filename to store the surface boxes and CFD grid points for plotting If the first character starts with a dollar sign the rest of the characters must be integers This integer is the identification number of an EXTFILE bulk data card where the filename is specified This feature allows for filenames up to 72 characters to be input Character or Blank See Remark 2 GSCALE A global scale factor applying to the x y and z of all CFD grid points Real gt 0 0 4 124 DATA DESCRIPTION OMITCFD FILESOL BLOCK ISTART IEND JSTART JEND KSTART KEND Remarks Charter string up to 16 characters to specify the filename to store the interpolated Cp and Mach numbers on the surface panels If the first character starts with a dollar sign the rest of the characters must be integers This integer is the identification number of an EXTFILE bulk data card where the filename is specified This feature allows for filenames up to 72 characters to be input Character or Blank Block index of the CFD mesh Integer gt 0 Indices of the I J K to define the CFD surface grid points The surface grid points are those between ISTART and IEND JSTART and JEND and KSTART and KEND where
19. 00 0 000000000 00 0 000000000 00 5 763368009E 02 000000000 00 0 000000000 00 0 000000000 00 0 000000000E 00 0 000000000E 00 000000000 00 1 495288195 04 0 000000000 00 1 115356274E 03 2 3 99 1 847709670 02 0 000000000E 00 0 000000000E 00 0 000000000E 00 0 000000000 00 0 000000000E 00 1 297997974E 03 0 000000000 00 4 428561904 03 0 000000000E 00 0 000000000E 00 0 000000000E 00 0 000000000E 00 0 000000000E 00 9 050600279E 03 0 000000000 00 0 000000000E 00 0 000000000E 00 0 000000000E 00 0 000000000E 00 0 000000000 00 2 976067064 04 0 000000000 00 2 228496429E 03 3 3 99 5 003520334E 02 0 000000000E 00 0 000000000E 00 0 000000000E 00 0 000000000E 00 0 000000000 00 6 703697305 02 0 000000000 00 3 474696162 02 0 000000000E 00 0 000000000E 00 0 000000000E 00 0 000000000E 00 0 000000000E 00 6 193062631E 02 0 000000000 00 0 000000000E 00 0 000000000E 00 0 000000000E 00 0 000000000E 00 0 000000000 00 2 439368145 03 0 000000000 00 1 811090503E 02 4 3 99 1 515793658E 01 0 000000000E 00 0 000000000 00 0 000000000E 00 0 000000000 00 0 000000000 00 6 854211102 02 0 000000000 00 2 003283120 02 0 000000000E 00 0 000000000E 00 0 000000000E 00 0 000000000E 00 0 000000000E 00 3 274867786E 02 0 000000000 00 0 000000000E 00 0 000000000E 00 0 000000000E 00 0 000000000E 00 0 000000000 00 1 419543836 03 0 000000000 00 1 052054613E 02 5 3 99 4
20. 000 00 04 000 00 00 000 15 42 000 00 00 000 00 21 000 00 03 000 00 00 000 00 00 Ood5n ooos uuoo Figure 2 3 ZONAIR Logfile Containing the Execution Summary Note that both the logfile and output file are overwritten upon resubmission of a ZONAIR job with the same input filename which are located within the same directory where the logfile and output already reside Therefore the user is cautioned to rename these files in the event they should be permanently saved How To RUNZONAIR 2 5 One exception to the output file being overwritten is if an output filename is specified when submitting a ZONAIR job that already exists For example if the file testcase out exists in the current directory and a ZONAIR job is requested as follows zonair testcase inp testcase out then the script file will prompt the user if the output file should be overwritten Plot Files ZONAIR provides a number of output plot files that can be viewed by several plotting programs Filenames for all output plot files are specified via the bulk data entries PLTAERO PLTCP PLTMODE PLTSURF and PLTTRIM Table 2 1 lists the output plot file capability of ZONAIR Table 2 1 ZONAIR Output Plot File Capability Associated Bulk Description Software Category Data Card Compatibility PATRAN TECPLOT Generates an ASCII text file for I DEAS plotting the aerodynamic model FEMAP ANSYS NASTRAN PATRAN TECPLOT Generates an
21. 13334013 6664013 000 023 6664015 Structural FEM Grid Points The first three comment cards initiated with a list the number of aerodynamic grid points GRID and quadrilateral CQUAD4 elements listed in the file If the FEMGRID entry of the PLTAERO bulk data card is set to YES then the number of structural grid points read in from the finite element input to the ZONAIR software system is also displayed and printed in this file A sample of the 7 2 PRESSURE COEFFICIENTS PLTCP An output data file of the pressure coefficients for all aerodynamic panels in the model can be generated with the PLTCP bulk data card see Figure 7 2 0 134022 0 120056 0 106089 0 0921233 0 0781571 0 0641909 0 0502248 0 0362586 0 0222924 0 00832625 Figure 7 2 Plot of Pressure Coefficient M 0 8 k 0 2 1st mode Re Cp The pressure coefficients and local Mach numbers for a specified flight condition specified by an AEROGEN bulk data card are generated For detailed descriptions of these options please see the PLTCP bulk data card description presented in Chapter 4 The PLTCP output plot file contains the aerodynamic pressures and local Mach numbers on each aerodynamic panel for the PATRAN I DEAS FEMAP and NASTRAN output cases or at each aerodynamic grid point for the TECPLOT output case PATRAN Compatible Output The PATRAN compatible output to display the pressure and local Mach number res
22. 4 210 BULK DATA DESCRIPTION WAKENET Normal vector of upper CSHEAR GRIDUi Normal vector of lower CSHEAR Therefore there are totally NX NY number of internally generated reference grid points denoted as Gi where j 1 NX and i 1 NY Two sets of CSHEAR elements are generated by the program one set on the upper surface of the wake surface and the other set on the lower surface Both sets of CSHEAR elements are connected by the same reference grid points except the connectivity sequence of the upper CSHEAR is Gji and whereas the lower CSHEAR is Gji and Gj This sequence gives two opposite normal vectors between the upper CSHEAR and lower CSHEAR It should be noted that for those CSHEAR elements immediately behind the trailing edge of the thick wing component the grid connectivity is GRIDU Gi and GRIDUj for the upper CSHEAR and GRIDLi 1 and GRIDL for the lower CSHEAR The SLOPE entry controls the direction of the wake lines at trailing edge of the wake surface See the following figure The angle of the wake line at the trailing edge of the thick wing component is defined by the GRIDA entry _ Wake line bl 7 zd Y Wake line LINE1 LINENY and LINETE used to add CROD CBAR elements along the two side edges the first and last wake lines and the trailing edge of the wake surface In the fol
23. ACQUIRE or ACQU retrieves an existing file containing AIC data Otherwise do not save or retrieve data File name up to 16 characters to specify the file name on which the AIC data is saved or retrieved If the first character starts with a dollar sign the rest of the characters must be integers This integer is the identification number of an EXTFILE bulk data card where the filename is specified This feature allows for filenames up to 72 characters to be input Character or Blank See Remark 4 4 118 DATA DESCRIPTION MACH Remark 1 The MACH bulk data card is referred to by an AEROGEN bulk data card However the existence of a MACH bulk data card in the Bulk Data Section automatically triggers the program to compute the aerodynamic matrices even if this MACH bulk data card is not referred to be any AEROGEN bulk data card Because computing aerodynamic matrices usually requires large amount of computer time the user should exclude any unused MACH bulk data card in the Bulk Data Section If RELAXW 0 no wake relaxation is performed Thus the wake shape generated by the WAKENET VORNET if any macroelements remains unchanged If VISCOUS 0 the inviscid vortex model of the line vortex CROD element is used which would yield infinite velocity influence coefficient at the center of the vortex core For VISCOUS 0 the aerodynamic forces and moments due to the skin friction drag will be computed If SAVE
24. PATRAN Compatible Output The PATRAN compatible output to display the interpolated mode shape is saved in two separate files The aerodynamic model is saved in the neutral file format while the interpolated mode shape nodal displacements are saved in a results file Both files will need to be imported into PATRAN to display the interpolated mode shape results A sample of the PATRAN compatible output files are shown in the following figures and are described below Neutral File of the Aerodynamic Model 25 0 0 1 0 0 0 0 0 ZONAIR AERODYNAMIC MODEL PATRAN NEUTRAL FILE OUTPUT 26 0 0 1 260 65 1 1 0 08 23 200009 09 28 2 5 1 1 0 2 0 0 0 0 0 0 100000000E 03 0 000000000E 00 0 000000000E 00 6 0 0000000 1 2 0 2 0 0 0 0 0 0 800000000E 02 0 120208158E 02 0 120208149E 02 ee 0G 6 0 0000000 Aerodynamic Grid Points 2 al 4 2 0 0 0 0 0 4 0 1 0 0 000000000E 00 0 000000000E 00 0 000000000E 00 2 3 4 2 2 4 2 0 0 0 0 0 4 0 1 0 0 000000000E 00 0 000000000E 00 0 000000000E 00 5 6 7 8 Aerodynamic Panels Results File of the Interpolated Mode Shape Displacement Results ZONAIR MODE SHAPE PLTMODE ID 10 MODE 1 FREQ 260 260 0 300000 02 259 3 FOR THREE DEGREES OF FREEDOM DX DY DZ SUBTITLE 2 10 0000000E 000 0000000E 000 0000000E 00 20 0000000 000 0000000 000 0000000 00 30 0000000 000 0000000 000 0000000 00 40 0000000E 000 0000000E 000 0000000E 00 7 Aero Grid Id s DX DY DZ Displacements at a
25. PLoT FILES 7 19 The comment title card list the index of the structural mode shape and the name of the structural finite element output file from which the structural finite element modes are read in i e file assigned by the ASSIGN Executive Command in the ASSIGN Executive Command Section 7 4 STATIC AEROELASTIC TRIM ANALYSIS RESULTS PLTTRIM An output data file of the static aeroelastic trim results can be generated with the PLTTRIM bulk data card Two types of output plot files and one ASCII text file can be generated through the use of the PLTTRIM bulk data card The plot files can be used to display the deformed aerodynamic model under flight loads e g Figure 7 4 a and or the resulting steady pressure distribution e g Figure 7 4 b An ASCII text file can also be output that contains the NASTRAN or I DEAS FORCE and MOMENT bulk data cards at the structural finite element grid points This output can be inserted into the NASTRAN or I DEAS model input deck to perform a detailed stress analysis using static structural analysis b a Figure 7 4 Sample Output Plot Files of the PLTTRIM Bulk Data Card a Deformed Aero Model and b Steady Pressure Distribution The output format for the deformed aerodynamic model is identical to that of the PLTMODE bulk data card please see Section 7 3 for a description of this output format except that both sides of the deformed aerodynamic model are included The outp
26. ZONAIR Positive 2 Deflection between Body amp Nose Nose 4 Body 2 at M 6 0 0 0492 0 0493 0 00612 C 0 0437 0 0408 C 0 0292 0 02806 9 gt 0 00668 lower CFL3D Op upper CFL3D Op lower ZONAIR Op upper ZONAIR CFL3D ZONAIR C 0 1637 0 1517 C 0 0857 0 08388 Cp 0 0537 0 057 INTRODUCTION 1 7 Multi Body Interference Busemann Biplane at a design Mach number M 1 75 and a 0 where the shock expansion theory predicts the nullification of wave drag due to the perfect cancellation of Mach waves Busemann Biplane at M 1 75 and a 0 Excellent agreement between ZONAIR and shock expansion theory is obtained ZONAIR MASS FLUX SHOCK EXPANSION THEORY x c C on Busemann Biplane at M 1 75 and a 0 Wave Drag Predictions The objective of the wind tunnel test is to determine the wave drag reduction of the GAF with a modified after body section denoted as H 18 from the baseline GAF denoted by H 17 Both wind tunnel models use an underbody blade sting for supplying the jet flow and have sealed inlets The difference in measured drag between these two models is assumed to be caused by the afterbody modification The purpose of this ZONAIR analysis is to validate this assumption by establishing four ZONAIR models H 17 blade sting H 18 blade sting H 17 witho
27. ZONAIR User s Manual Engineering Software for Aerodynamics and Flight Loads SESS ZONA TECHNOLOGY INC ZONAIR Version 4 4 USER S MANUAL ZONA 02 13 October 2011 ZONA Technology Inc rights reserved Ninth Edition 10 11 MSC PATRAN is a registered trademark of the MSC Software Corporation NASTRAN is a registered trademark of the MSC Software Corporation MSC NASTRAN is an enhanced proprietary version developed and maintained by the MSC Software Corporation MSC ARIES is a trademark of MSC I DEAS and FEMAP are trademarks of Structural Dynamics Research Corporations TECPLOT is a trademark of AMTEC Engineering Other product names and trademarks are the property of their respective owners DISCLAIMER THE MATERIAL PRESENTED IN THIS TEXT IS FOR ILLUSTRATIVE AND EDUCATIONAL PURPOSES ONLY AND IS NOT INTENDED TO BE EXHAUSTIVE OR TO APPLY TO ANY PARTICULAR ENGINEERING PROBLEM OR DESIGN ZONA TECHNOLOGY INC ASSUMES NO LIABILITY OR RESPONSIBILITY TO ANY PERSON OR COMPANY FOR DIRECT OR INDIRECT DAMAGES RESULTING FROM THE USE OF ANY INFORMATION CONTAINED HEREIN gt ZONA TECHNOLOGY INC TEC ol INOLOGY ZONA Technology Inc 9489 E Ironwood Square Drive Scottsdale AZ 85258 Tel 480 945 9988 Fax 480 945 6588 e E mail info zonatech com This page is intentionally left blank TABLE OF CONTENTS Page FOR PWA DECEM Foreward 1 1 0 INTRODUCTION 3 2 ree
28. on the body It can be used to improve the smoothness of the grid points at the wing body junction In the following figure Figure a depicts a wing body configuration without the wing thickness Figure b presents a wing body configuration with the wing thickness and CANTR 0 0 Figure c is the same as Figure b except CANTR 40 CANTR 0 Wing Mean Plane Dihedral angle BULK DATA DESCRIPTION 4 177 TRIM TRIM Static Aeroelastic Trim Analysis Description Defines the flight condition rigid body mass matrix trim degrees of freedom and trim variables for a trim analysis To include the structural flexibility effects in the trim analysis it is required to specify the ASSIGN FEM and SOLUTION 1 Executive Control Commands Otherwise the trim analysis is performed on the rigid aircraft Format and Example 2 3 4 5 6 7 8 9 T 10 TRIM TRIMID IDAERO IDOBJ IDCONS RHOX RHOY RHOZ oo 0 X TRNACC PDOT ODOT RDOT LOADSET CON IDVAR1 VAL1 IDVAR2 VAL2 era 0 0 aos 4 mer 2 oo onem m Le d d Field Contents TRIMID Unique set identification number Integer gt 0 See Remark 1 IDAERO Identification number of an AEROGEN bulk data card that defines the flight condition used for the static aeroelastic trim analysis Integer gt 0 See Remark 2 QINF Dynamic pressure Real gt 0 0 See Remark 3 IDOBJ Identification n
29. 3177 UNIT SYSTEM ISO END UNIT DEGREE END DEGREE K MATRIX DOF T 1230923559613264 04 6983785713017072D 04 2457474668222889D 03 1091649015086483D 03 oo 0 3686414966027151D 04 2023261010701697D 04 0 1130354829300728D 03 3635281838273271D 04 2419062914082075D 03 7831696499717704D 04 4604977332201705D 04 9274910202744236D 04 3 14 EXECUTIVE CONTROL SECTION ASSIGN FEM DOF 2 0 1309670841427416D 03 7472762150226767D 04 5447145357492463D 06 0 8176428928352975D 05 1808144454036312D 05 2884186353798238D 04 DOF 2 0 3686414966027151D 04 0 1628147041567078D 03 M MATRIX DOF 1 5497212390994216D 00 9254207643250023D 6852211940217012D 1480555993560104 3575698764857194 4089610594615323 4511975103434207D 3460616633478488D 0 1245350190700635D 0 1008308020411519D Lu o OY 1 OY OY Ui Ui 9446850040509963D 2718403166413960D 14 MONVAL al TITLE KIND DISP NAME SELECT WING NODE 2 TYPE TX COORD 0 2940557999999999D 00 0 0000000000000 p x c o oo 9446850040509963D 1457946990131992D 6256388636327603D 7164950056870456 1365281585702371 1493488492598782 2422683635736750 3662570463927595 3208899617378191 9849299110673004D 4488872714871719D 04 4713285201889093D 04 3868854191317292D 05 1887274213933592D 05 11653965
30. 65 F FEPOINT 1 0000E 02 0 0000 00 0 0000 00 202 8 0000E 01 1 2021E 01 1 2021E 01 207 Grid Point 8 0000E 01 0 0000 00 1 7000E 01 206 Identification Numbers 1 0000E 02 0 0000E 00 0 0000 00 201 1 0000E 02 0 0000E 00 0 0000 00 203 Ts Aerodynamic Grid Points X Y Z 1 2 3 4 Aerodynamic Connectivity 5 6 4 8 Information aero panels 9 10 11 12 e g the first line connects the 1st 2nd 3rd and 4th 13 14 15 16 aero grid points listed above 17 18 19 20 TITLE lists the requested structural mode index and the name of the structural finite element output file from which the structural finite element modes are read in 1 file assigned by the ASSIGN Executive Control Command in the ASSIGN Executive Command Section VARIABLE defines the variable names associated with the column data X X coordinate of the aerodynamic grid point Y Y coordinate of the aerodynamic grid point Z Z coordinate of the aerodynamic grid point EXTID External grid point identification number 7 16 PLOT FILES ZONE I J F FEPOINT specifies information for the current zone number of aerodynamic grid points listed in the plot file number of aerodynamic panels listed in the plot file e DEAS Compatible Output finite element zone specification The I DEAS compatible output is saved in the universal file format Data sets 781 and 780 are used to output the aerodynamic grid points and panels respectively Data set 55 is used to output
31. B B 1 6 Free Format In free format the data entries must be separated by commas separation by a blank is not allowed The following shows the AEFACT bulk data card with one continuation line in free format Indicates an empty field default value will be used 100 0 2 0 3 0 4 0 5 0 6 0 7 A A 0 8 0 9 There are several rules for free format Free format data must start in column 1 Each data entry for all three types of data integer real and character cannot exceed 8 columns To skip one entry use two commas in succession and so on Fixed format and free format can be mixed For example the following is acceptable BULK DATA DESCRIPTION 4 3 AEFACT 100 0 0 0 2 01 53 0 4 0 5 0 6 0 7 A A 0 8 0 9 42 BULK DATA CARDS SUMMARY AND INTERRELATIONSHIPS This section contains a summary of all the bulk data cards in the ZONAIR system separated into logically related groups according to the ZONAIR engineering modules These modules are shown the Figure 4 1 Note that the SPLINE module is invoked only if the Executive Control Command SOLUTION 1 is specified that activates the inclusion of structural flexibility effects for the trim analysis FEM Module i Geometry Module ModalData Importer ASSIGN FEM Executive Control Co
32. Figure 1 3 Subdivision of Figure 1 2 Elementary Singularity Distribution at Quadrilateral Panel into Sub Grid Points triangular Panels Furthermore because the four corner points of a quadrilateral panel may not locate on the same plane each quadrilateral panel is subdivided into six triangular panels for the continuity of panel geometry Figure 1 3 At each panel both Dirichlet boundary condition 0 and Neumann boundary condition 99 X imposed for soling the source and doublet strengths Figure 1 4 Also the zero force condition 0 is imposed on the wake to satisfy the wake condition ay MESE e ic 634 ute emu t 9 or 70 Wake W si Figure 1 4 Dirichlet and Neumann Boundary Conditions on Panels and Zero Force Condition on Wake Surface 1 2 INTRODUCTION 13 NO REQUIREMENT FOR MODELING WAKE SURFACES Unlike other high order panel methods such as PANAIR VSAERO and QUADPAN where the wake surfaces must be explicitly modeled ZONAIR requires only the specification of the line segments along the trailing edge of the wing and body where the wake surface starts no wake surface modeling 1s required by ZONAIR These line segments for wake modeling are shown in Figure 1 5 Internally ZONAIR sweeps these line segments to infinity and creates a flat wake surface Because an exact solution can be obtained by integrating the wake integral from the line segment to infinity the wake
33. INPFILE The name of the input file where the flowfield point mesh is stored Character OUTFILE The name of an output file where the aerodynamic solutions are stored Note that the format of the output data 1s also stored according to the entry FORM Remarks 1 The FLOWPT bulk data card is not referred to by any other bulk data cards Its existence in the Bulk Data Section triggers the program to generate aerodynamic solution at flowfield points 2 The flowfield solutions are computed based on the flight condition specified by the AEROGEN bulk data card with identification number IDAERO 3 For the PLOT3D formatted file all data are written in the free format For the PLOT3D unformatted file all data are stored in the binary format BULK DATA DESCRIPTION 4 87 FLOWPT CardSet1 BLK NBLK Number of blocks of the mesh Integer gt 0 Example 2 Card Set2 IMAX L JMAX L KMAX L L 1 NBLK Eh IMAX JMAX and KMAX are the number of grid points along the I J and K directions of each block respectively Integer gt 0 KMAX L i L 1 Card Set 3 1 I 1 IMAX L j l JMAX L k 1 KMAX L 1 1 IMAX L j 1 JMAX L k 1 KMAX L 2 1 I 1 IMAX L j 1 JMAX L k 1 KMAX L x 1 k x i j k 1 and z 1 k are the x y and z locations of the grid points 1 Real For FORM UDP3D IUDP3D and z are in the double
34. PANLST2 PANLSTS3 bulk data card that lists the aerodynamic panel identification numbers Integer gt 0 SETG The identification number of a SETi bulk data card that lists the structural grid points to which the spline 15 attached Integer gt 0 DZ Linear attachment flexibility Real 2 0 0 See Remark 3 EPS Multiplication factor to obtain a small tolerance to detect any duplicated location of structural grid points The tolerance is computed by EPS REFC where REFC is the reference chord defined in the AEROZ bulk data card Real gt 0 0 Default 0 01 See Remark 4 Remarks 1 is only used for error output SPLINE1 is used only for computing the flexible loads 2 If no CP is specified the plane defined by the macroelement specified in the PANLSTi bulk data card is used for the spline plane 3 The attachment flexibility units of area is used for smoothing the interpolation If DZ 0 0 the spline will pass through all deflected grid points If DZ is much greater than the spline area a least square plane fit will be applied Intermediate values will provide smoothing 4 If any two or more structural point locations projected on the spline plane are nearly the same the spline matrix is singular EPS is used to detect this condition BULK DATA DESCRIPTION 4 165 SPLINE2 SPLINE2 Beam Spline Method Description Defines a beam spline method for the BODY7 or CAERO7 macroelement The SPLINE2 bulk data
35. PLTCP 3000 MODE 1 MACH 8000 K 2000 VARIABLE X Y Z RE CP IM CP EXTID ZONE I 91 J 65 F FEPOINT 1000E 03 0000E 00 0000E 00 7643E 04 2361E 03 201 1000E 03 0000E 00 0000E 00 5331E 04 1644E 03 202 1000E 03 0000E 00 0000E 00 2541E 05 3619E 05 203 1000E 03 0000E 00 0000E 00 5529E 04 1649E 03 204 1000E 03 0000E 00 pde 7531E 04 2300E 03 205 S Grid Point Aerodynamic CP Local Mach Identification Grid Points X Y Z Numbers 2 7 6 1 3 8 7 2 m 4 9 8 3 Aerodynamic Connectivity 5 10 9 4 TUNI Information aero paneles 7 12 11 6 e g the first line connects the 2nd 7th 6th and Ist aero grid points listed above 7 10 PLOT FILES TITLE VARIABLE X Y 7 RE CP IM CP EXTID ZONE I J F FEPOIN lists the PLTCP bulk data card identification number defines the variable names associated with the column data X coordinate of the aerodynamic grid point Y coordinate of the aerodynamic grid point Z coordinate of the aerodynamic grid point Real component of the pressure result Imaginary component of the pressure result External grid point identification number specifies information of the current zone the Tecplot input can be broken up into multiple zones only one zone is used to define the pressure output number of aerodynamic grid points listed in the plot file number of aerodynamic panels listed in the plot file T finite element zone specification e DEA
36. RHO Non dimensionalized density Real RHOU Non dimensionalized momentum along x Real RHOV Non dimensionalized momentum along y Real RHOW Non dimensionalized momentum along z Real E Non dimensionalized total energy Real Repeat card set 2 NSGRID times BULKDATA DESCRIPTION 4 107 INPCFD1 Otherwise Card Set 2 X y z RHO V W Cp Po M S Free Format 2 and z location of the surface grid point Real RHO Non dimensionalized density Real U V W Non dimensionalized velocity components along x y and z directions Cp respectively Real Po Pressure coefficients Real M Non dimensional pressure Real S Local Mach number Real Entropy Real Repeat card set 2 NSGRID times Card Set 3 IDS1 IDS2 IDS3 IDS4 Free Format IDS1 IDS2 IDS3 Grid point indices of the four corner points of the surface elements Integer Note that for IDS4 triangular element setting IDS3 IDS4 is recommended Repeat card set 3 NSELEM times 4 The objective of the FILEMESH entries is to output a graphical file that allows the user to verify the overlapping between the ZONAIR surface boxes and those CFD grid points near the surface mesh 5 The surface box model includes BODY7 macroelement as well as the upper and lower surface of the macroelements whose airfoil sections are defined by the PAFOIL7 PAFOILS bulk data card 6 Nomenclature M free stream Mach num
37. ROLL Represents the rolling mode For SYM ASYM LABEL can be one of the character strings FORAFT PLUNGE PITCH YTRANS YAW or ROLL Character Default PITCH Identification number of a LOADMOD bulk data card to define the component forces moments Integer gt 0 See Remark 3 Dynamic pressure that multiplies the component forces moments computed by the program Real 0 0 See Remark 4 Multiplication factor to the forces moments specified in the entries RFORCE1 Real See Remark 5 The first given set of component forces moments Real Not used Multiplication factor to the forces moments specified in the entries 2 Real The second given set of component forces moments Real Not used 1 WTIFRC bulk data card defines a set of component force derivatives with respect to a mode The set of component force derivatives is used to generate a force moment correction matrix 2 The entries TYPE and LABEL jointly define the type of mode that is used to obtain the given set of component forces and moments For instance if the component forces and moments are measured on a rigid aerodynamic wind tunnel model at an angle of attack TYPE RIGID and LABEL PITCH are recommended 3 LOADMOD bulk data card will jointly generate a component load integration matrix L such that 5 given 4 218 DATA DESCRI
38. SAVE the AIC matrices will be saved on an unformatted data file with file name FILENM as the archival data entity If SAVE ACQUIRE or ACQU the AIC matrices will be retrieved from the data file with name FILENM In this case a large amount of computing time can be saved BULK DATA DESCRIPTION 4 119 MATBODY MATBODY Aerodynamic Component Description Defines an aerodynamic component by grouping a set of CQUAD4 CTRIA3 panels Format and Example 1 2 3 4 5 6 7 8 9 10 MATBODY LABEL TYPE NOSEGRD BLUNT NAXIS wrap 00 CONT e oe oe Toe om pee Field Contents MID Unique identification number Integer gt 0 See Remark 1 LABEL Unique character string to define the name of the aerodynamic component Character TYPE Character string either WING or BODY used only for hypersonic aerodynamics Character See Remark 2 NOSEGRD Identification number of a GRID bulk data card with entry PS 0 or blank to specify the grid point located at the nose of the body Used only if TYPE BODY Integer BLUNT Character string either YES or NO For BLUNT YES and TYPE BODY the nose of the body is a blunt nose For BLUNT YES and TYPE WING the leading edge of the wing is a round leading edge Used only for hypersonic aerodynamics Character NAXIS Define a set of NAXIS x NRAD panels that represent the no
39. UNIX Multiple jobs can be submitted in the UNIX environment submitting multiple jobs is optional not a requirement Simply initiate the ZONAIR script file multiple times in succession For example to submit two jobs called test1 inp and test2 inp type the following at the command prompt zonair testl inp and press the return key followed by zonair test2 inp and press the return key Two jobs will be submitted each with a unique process id type ps a to see a listing of all running jobs on the system Multiple jobs can be submitted from either the same directory or different directories Associated output files will be placed in the directories from which the input jobs were submitted Any AIC files to be read in for a How TORUNZONAIR 2 7 restart run process must also be located in the directory from which the input job is submitted At the end of each batch job process the script file will notify the user of job termination by a beep sound As a final note the input output decks are in ASCII text format and can be viewed and or modified with any editor on the host system such as the vi editor UNIX Script File Process 1 Acquire the input filename from standard input 2 Check if input file exists locally 3 Acquire the output filename if specified in the command line 4 Establish an output filename if not found in step 3 and logfile filename 5 Check the run time database directory path specified
40. and z i j k precision Omit Card Set 4 for FORM P3D UP3D or UDP3D Card Set 4 IBLANK j k i 1 IMAX L j 1 JMAX L 1 KMAX L Ec IBLANK i j k are the indices of each grid point for blanking Integer Repeat Card Set 3 and Card Set 4 NBLK times L L 1 For output five variables namely p pU pV pW and E are stored in the output file OUTFILE Where p is the density U V and W are the velocities and E is the energy Note that these five variables are computed based on the assumption that P 1 1 4 where P is the freestream pressure 4 For FORM NASTRAN the flowfield point mesh is an unstructured grid and in the NASTRAN bulk data card format called GRID File INPFILE can contain other NASTRAN bulk data cards but only the input card starts with GRID is read in Format 1 2 3 5 6 7 8 9 10 GRID ID X Y 2 Example GRID 101 1 0 0 0 3 70 4 88 BULK DATA DESCRIPTION FLOWPT Field Content ID Unique Identification number of the grid Integer gt 0 2 Location of the flowfield point Real For output the NASTRAN TEMP bulk data cards are used to store the aerodynamic solutions U V W C and Mach numbers For FORM FREE the flowfield point mesh is an unstructured mesh and its grid points are listed in a free format according to the following input instruction Ca
41. gt 0 L 1 Card 2 IDG x y z Format IDG Identification of the grid point Integer X Y Z x y and z location of the grid point Real Repeat Card 2 for NGRID times L L 1 L 1 Card 3 IDP ID1 ID2 ID3 ID4 Format IDP Identification number of the panel Integer ID1 ID2 Identification number of the grid points at the four corners ofthe Integer ID3 ID4 panel Repeat Card 3 for NPANEL times L L 1 BULK DATA DESCRIPTION 4 95 GRID GRID Grid Point Description Defines the location of a surface grid point or a reference grid point Format and Example Field Contents ID Grid point identification number Integer gt 0 See Remark 1 CP Identification number of coordinate system in which the location of the grid is defined Integer 7 0 or Blank See Remark 2 Xi Location of the grid point in coordinate system CP Real PS Flag for indicating a surface grid point or a reference grid point PS 0 or blank the grid is a surface grid PS 3 0 the grid is a reference grid point Integer See Remark 3 Remarks 1 All grid point identification numbers must be unique 2 The meaning of X1 X2 and X3 depend on the type of coordinate system CP as follows TYPE X2 X3 Rectangular Y Z Cylindrical 0 deg Z Spherical 0 deg 9 deg Note Also see CORDij entry descriptions 3 There are two types of grid points t
42. k 1 KMAX L yG j k i 1 IMAX L j 1 JMAX L k 1 KMAX L z i j k i 1 IMAX L j 1 JMAX L k 1 KMAX L otherwise x i j k i 1 IMA X L j 1 JMAX L k 1 KMAX L yG j k i 1 IMAX L j 1 JMAX L k 1 KMAX L z i j k i 1 IMAX L j 1 JMAX L k 1 KMAX L IBLANK j k i 1 IMAX L j 1 JMAX L k 1 KMAX L x 1 k y 1 k z 1 j k x Lj k 1 and 2 1 1 the x y and z locations of the grid points and Real For FORMCFD UDP3D x y and z are in double precision IBLANK i j k IBLANK i j k are the indices of each grid point for blanking Integer Repeat Card Set 3 NBLK times L L 1 6 The CFD solution must be computed either by the Euler solver or the Navier stokes solver Its format is shown as follows Card Set 1 NBLK Format NBLK Number of blocks of the CFD mesh Integer gt 0 BULK DATA DESCRIPTION 4 103 INPCFD L 1 Card Set 2 IMAX L JMAX L KMAX L L 1 NBLK IMAX L IMAX JMAX and KMAX are the number of grid points along the I J and JMAX L directions of each block respectively Integer gt 0 KMAX L Card Set 3 FMACH ALPHA RE TIME Format FMACH Mach number Real or double precision ALPHA Angle of Attack RE Reynolds number TIME Time step RHOG j k i 1 IMAX L j 1 JMAX L k 1 KMAX L Format RUG j K i 1 IMAX L j 1 JMAX L k 1 KMAX
43. 01 0 0000 00 0 0000 00 0 0000E 00 0 0000E 00 1 6393 04 1 1190 01 4 3495 04 3 0469E 03 7 2485E 04 6 9882E 03 0013 5 1500E 00 1 5780E 06 1 6500E 01 0 0000E 00 0 0000E 00 0 0000E 00 0 0000E 00 1 8241E 04 9 6145E 00 4 2741E 04 2 8185E 04 7 1617E 04 7 0603E 04 0014 8 8000E 00 1 5780E 06 1 6500E 01 0 0000 00 0 0000 00 0 0000E 00 0 0000E 00 1 6958E 04 5 2334E 01 4 2869E 04 5 1457E 03 7 1225E 04 5 0333E 04 0015 1 5000 00 3 1560E 06 1 6500 01 0 0000 00 0 0000E 00 0 0000 00 0 0000E 00 2 4384E 04 3 1922E 00 4 1101E 04 2 3071E 04 7 2579E 04 5 3624E 04 0016 5 1500 00 3 1560E 06 1 6500 01 0 0000 00 0 0000E 00 0 0000E 00 0 0000 00 8 2579 04 4 0963 02 2 2161E 04 5 4569E 05 7 0172E 04 1 9318E 06 0017 8 8000 00 3 1560E 06 1 6500 01 0 0000 00 0 0000E 00 0 0000E 00 0 0000E 00 4 3647 04 3 4296E 02 3 4939 04 2 0096E 05 7 0979E 04 5 7587E 05 0018 1 5000E 00 0 0000 00 3 0000E 01 0 0000 00 0 0000E 00 0 0000 00 0 0000 00 4 1349 04 7 0364 01 6 8519E 04 9 0037E 02 1 2242E 05 6 5616E 02 0019 5 1500 00 0 0000E 00 3 0000E 01 0 0000 00 0 0000E 00 0 0000 00 0 0000E 00 3 8741E 04 2 8312 00 6 4171E 04 2 4243 03 1 1407E 05 4 9951E 03 0020 8 8000E 00 0 0000 00 3 0000 01 0 0000 00 0 0000E 00 0 0000E 00 0 0000E 00 3 7622E 04 7 3016E 01 6 2407 04 1 7534E 03 1 1090 05 3 0921E 03 0021 1 5000 00 1 5780E 06
44. 01 0 0000000000000000D 00 0 0000000000000000D 00 10102 1 T 1 3 0000000000000000D 01 3 3333000183105467 01 0 0000000000000000D 00 10103 1 jb 1 3 0000000000000000D 01 6 6666999816894527D 01 0 0000000000000000D 0010104 1 1 T 3 0000000000000000D 01 1 0000000000000000D 02 0 0000000000000000D 0010201 1 T 1 5 3333000183105472 01 1 6666999816894532 01 0 0000000000000000D 0010202 1 1 2 5 3333000183105472D 01 4 4444000244140626D 01 0 0000000000000000D 0010203 1 1 d 5 3333000183105472D 01 7 2222000122070308D 01 0 0000000000000000D 00 10204 1 1 5 3333000183105472D 01 1 0000000000000000D 02 0 0000000000000000D 00 10301 1 1 2 7 6666999816894527D 01 3 3333000183105467 01 0 0000000000000000D 00 10302 1 T 1 7 6666999816894527D 01 5 5555000305175781D 01 0 0000000000000000D 00 10303 1 2 7 6666999816894527D 01 7 7777999877929691D 01 0 0000000000000000D 00 10304 1 1 7 6666999816894527D 01 1 0000000000000000D 02 0 0000000000000000D 00 10401 1 T 1 1 0000000000000000D 02 5 0000000000000000D 01 0 0000000000000000D 00 10402 1 als a 1 0000000000000000D 02 6 6666999816894527D 01 0 0000000000000000D 00 10403 1 1 1 0000000000000000 02 8 3333000183105490D 01 0 0000000000000000D 00 10404 1 111 1 1 0000000000000000D 02 1 0000000000000000D 02 0 0000000000000000D 00 20000 2 1 1 0 0000000000000000D 00 3 3333000183105467 01 0 0000000000000000D 00 i L 2414 1 B C 0 MODE 1 DISPLACEMENT 1 1 NONE OUGV1 REAL MODE SHAPE ANALYSIS DATE 07 27 99
45. 04 READ MODULE EXECUTIVE CONTROL SECTION 3 7 ASSIGN FEM MODE NO ORDER OPWNE EIGENVALUE CYCLES POINT ID 10101 10102 10103 10104 10201 10202 10203 10204 10301 10302 10303 10304 10401 10402 10403 10404 20000 EIGENVALUE CYCLES POINT ID 10101 10102 10103 10104 10201 10202 10203 10204 10301 10302 10303 10304 10401 10402 10403 10404 20000 EIGENVALUE CYCLES POINT ID 10101 10102 10103 10104 10201 10202 10203 10204 10301 10302 10303 10304 10401 10402 10403 10404 20000 EIGENVALUE CYCLES POINT ID 10101 10102 10103 10104 10201 ph EXTRACTION EIGENVALUE Mo oS UD 0D 399865E 02 401589 03 316370 04 341672 04 008154 05 8 399865 02 4 612711 00 Q00000000aGaacaaoooodq Tl 5 401589E 03 1 169717E 01 TYPE QAAAARAAAAAAAAAARAAAA Ooooooooooooooooo TE 4 316370E 04 3 306583E 01 TYPE Ooooooooooooooooo Tl 7 341672 04 4 312386 01 ooooo TL ooooo REAL REAL REAL OOo ocdOcoococooooooooo OoOoocoogdGodooocoooooo OG ogoccococcocooooooodocdso E ooooo
46. 1 The PSHEAR bulk data card is referred to by a CSHEAR bulk data card The boundary condition of the wake surface is that the potential is constant along each wake line In the following figure the symbols 2 and represent the potential at the surface grid points GRIDA and GRIDB respectively The entries GRIDA SIDEA GRIDB and SIDEB impose the condition by specifying SIDEA 1 and SIDEB 3 So that and Perms BULK DATA DESCRIPTION 4 149 PSHEAR 4 150 GRIDB Wakeline i 0 GRIDA 3 gt For wake surface attached to the trailing edge of a thick wing component normally there is only CQUAD4 CTRIA3 panel on which both the surface grids GRIDA and GRIDB are located In this case this panel can be automatically identified by the program and the entry ATTACH can be blank However if there are two CQUAD4 CTRIA3 panels on which GRIDA and GRIDB are located the identification number of one of these two panels must be specified by ATTACH In the following figure there are two CQUAD4 s ID 101 and 102 on which GRIDA and GRIDB are located For a CSHEAR panel with grid sequence G1 G2 G3 and G4 which define the normal vector as shown in the figure ATTACH 101 must be selected because CQUADA ID 101 is located above the CSHEAR panel above and below are defined by the normal vector of the CSHEAR panel CQUADA 101 Normal vector CQUAD
47. 1 2 3 4 5 6 7 8 9 10 Field Contents CID Coordinate system identification number Integer gt 0 Gi Grid point identification number G can be either a surface grid or a reference grid Integer gt 0 GI G2 G3 Remarks 1 Coordinate system identification numbers on all CORDIR CORDIC CORDIS CORD2R CORD2C and CORD2S entries must be unique 2 The three points G1 G2 and G3 must be noncollinear 3 The location of a grid point P in the sketch in this coordinate system is given by R 0 where 0 and are measured in degrees 4 displacement coordinate directions at P are dependent on the locations of P as shown above by u Us 4 58 BULK DATA DESCRIPTION CORDIS 5 Points on the polar axis may not have their displacement direction defined in this coordinate system since an ambiguity results 6 Oneor two coordinate systems may be defined on a single entry BULK DATA DESCRIPTION 4 59 CORD2C CORD2C Cylindrical Coordinate System Definition Form 2 Description Defines a cylindrical coordinate system by reference to the coordinates of three grid points The first point defines the origin The second point defines the direction of the z axis The third lies in the plane of the azimuthal origin The reference coordinate system must be independently defined Format and Example x 2 3 4 5 6 7 8 9 10
48. 4 5 Bulk Data Interrelationship for Aeroheating Analysis 4 2 5 INPUT FOR STATIC AEROELASTIC TRIM ANALYSIS TRIM MODULE The function of the static aeroelastic trim analysis is to solve the trim system and compute the flight loads The solution of the trim system requires the balance of the inertial loads due to the accelerations of the trim degrees of freedom X Y Z p qandi see Figure 4 6 and the aerodynamic loads generated by the trim variables a D p q r control surface deflections etc It should be noted that the structural flexibility effects are included in the trim analysis only if the Executive Control Command SOLUTION 1 is specified and the structural finite element modal solution is imported via the ASSIGN Executive Control Command BULK DATA DESCRIPTION 4 11 REFX REFY REFZ Figure 4 6 Definition of Trim Degrees of Freedom There are several major differences between the ZONAIR solution technique and the NASTRAN solution technique in solving the trim system ZONAIR employs the modal approach to solve the trim system of the flexible aircraft whereas NASTRAN uses the direct method that includes all structural degrees of freedom in the trim system The modal approach assumes that the structural deformation xj can be approximated as tg PHG ig where PHG is the modal matrix containing the lower order modes of the structural finite element model and 4 are the generalized
49. 46 CASE CONTROL SECTION Comment Statement Description Used to insert comments into the Case Control Section Format followed by any characters up to column 80 Example The next command is FLUTTER Remarks 1 must appear in the first column 2 command be repeatedly used anywhere the Case Control Section CASE CONTROL SECTION 3 47 This page is intentionally left blank 3 48 CASE CONTROL SECTION Chapter 4 ZONAIR BULK DATA SECTION The Bulk Data Section begins right after the BEGIN BULK Case Control Command and ends at a bulk data card ENDDATA The Bulk Data Section contains bulk data cards that specify the geometry of the aerodynamic model spline for displacement and force transferal between the structural finite element grid points and aerodynamic panels for static aeroelastic analysis the Mach numbers aerodynamic methods and flight conditions for aerodynamic result generation disciplines aerodynamic analysis aeroheating analysis trim analysis etc to be analyzed other miscellaneous inputs 4 1 FORMAT OF BULK DATA CARDS The format of bulk data cards is identical to that in NASTRAN except for the so called Large Field Entry 1 16 characters wide which is not allowed for definition of Large Field Entry please see NASTRAN User s Manual The bulk data card contains ten fields per input data entry The first field contains the character name of
50. 54387E 03 9 40881E 03 0 00000E 00 10303 G 0 00000E 00 0 00000E 00 6 02194E 01 7 47848E 03 9 98555E 03 0 00000E 00 10304 G 0 00000E 00 0 00000E 00 8 25272 01 7 31122E 03 1 00018E 02 0 00000E 00 10401 G 0 00000E 00 0 00000E 00 4 88816E 01 6 88055E 03 9 98074E 03 0 00000E 00 10402 G 0 00000E 00 0 00000E 00 6 58736E 01 7 41750E 03 1 03422E 02 0 00000E 00 10403 G 0 00000E 00 0 00000E 00 8 30776E 01 7 23585E 03 1 01161E 02 0 00000E 00 10404 G 0 00000E 00 0 00000E 00 1 00000E 00 7 59407E 03 1 01071E 02 0 00000E 00 20000 G 0 00000E 00 0 00000E 00 0 00000E 00 0 00000E 00 0 00000E 00 0 00000E 00 ASTROS VERSION 21 2 B04 10 09 P 9 FINAL ANALYSIS SEGMENT DEMO CASE MODES ANALYSIS BOUNDARY 1 MODE 2 REAL EIGENVECTOR FOR MODE 2 EIGENVALUE 4 40079E 03 RAD S 2 CYCLIC FREQUENCY 1 05581E 01 HZ POINT ID TYPE TL T2 T3 R1 R2 R3 10101 G 0 00000E 00 0 00000E 00 9 99443E 02 1 37041 02 5 07218E 03 0 00000E 00 10102 G 0 00000E 00 0 00000E 00 2 77751 03 1 81102 04 6 32624 04 0 00000E 00 10103 G 0 00000E 00 0 00000E 00 3 69295E 01 9 94513 03 2 12634E 02 0 00000E 00 10104 G 0 00000E 00 0 00000E 00 1 00000E 00 1 52928 02 1 62984E 02 0 00000E 00 10201 G 0 00000E 00 0 00000E 00 2 96668 01 9 29880 03 3 80525E 03 0 00000E 00 10202 G 0 00000E 00 0 00000E 00 1 10681E 01 1 36695 02 9 48454 03 0 00000E 00 10203 G 0 00000E 00 0 00000E 00 2 01263E 01 1 24942 02 1 27435E 02 0 00000E 00 10204 G 0 00000E 00 0 00000E 00 6 35580E 01 1 5
51. 641623764 02 0 000000000 00 0 000000000E 00 0 000000000E 00 0 000000000E 00 0 000000000 00 8 665747224E 03 0 000000000 00 1 854310840 02 0 000000000E 00 0 000000000E 00 0 000000000E 00 0 000000000E 00 0 000000000E 00 2 731625756E 03 0 000000000 00 0 000000000E 00 0 000000000E 00 0 000000000E 00 0 000000000E 00 0 000000000 00 1 271699994 03 0 000000000 00 9 484510803E 03 6 T 1 310664892 00 3 22 EXECUTIVE CONTROL SECTION ASSIGN MATRIX For Sparse and ASCH Format FORM SFORMAT Record 1 NCOL NROW NF NTYPE NAME 418 8 NCOL Number of columns NROW Number of rows NF Form of matrix NF 2 General rectangular matrix NF 6 Symmetric matrix Only the upper triangular part including diagonals is input NTYPE Type of matrix NTYPE 1 Real single precision NTYPE 2 Real double precision NTYPE 3 Complex single precision NTYPE 4 Complex double precision NAME Character string up to 8 characters If no MNAME c is specified these characters are used as the name of the matrix Record 2 ICOL IZERO NW 318 ICOL IZERO NW Column Number Must be 0 Number of words in the column For a complex matrix there are two values per row Record 3 IS 18 IS IROW 65536 L 1 where IROW is the row position of the first term in the string and L is the length of the string For example a string of six words beginning in row 4 has IS 458756 L and I
52. 64A 65 65 66 67 Character Default 4 For TY PE USER If PROFILE LINEAR use linear interpolation to interpolate the airfoil section from the user defined airfoil thickness distribution Otherwise use cubic spline for interpolation Character Default CUBIC 4 90 BULK DATA DESCRIPTION FOILSEC FIRST For TYPE NACA SECOND PROFILE 4 NACA 4 digit airfoil THIRD FIRST the maximum camber in percent chord FOURTH SECOND the maximum camber location in tenths of chord FIFTH THIRD the airfoil thickness in percent chord FOURTH and FIFTH not used Example NACA 2412 PROFILE 4M 4 digit modified airfoil FIRST the maximum camber in percent chord SECOND the maximum camber location in tenths of chord THIRD the first and second digit of the appended number the first digit 0 3 6 or 9 which indicates leading edge radius index number the second digit indicates the location of maximum thickness in tenths of chord FOURTH and FIFTH are not used Example NACA 2412 04 PROFILE 5 5 digit airfoil FIRST the design lift coefficient C FIRST 3 20 SECOND the twice the location of maximum camber in tenths of chord SECOND 20 THIRD 0 a 1 a reflexed trailing edge FOURTH the airfoil thickness in percent chord FIFTH is not used Example NACA 24012 PROFILE 5M 5 digit modified airfoi
53. 7 1 THEJAVA a pp p pau aua 2 10 21 2 SERVER INSTALLATION AND OPERATIONS eee en n nennen nnne nnn nnn annua 2 10 2 7 3 ENVIRONMENT 5 44 0440 2 10 2 7 4 THE ZONA LICENSE 00 0 000001 1 nene 2 11 2 7 5 LOCKED TOKENS AND THE CLEANUP UTILITY 000cc00ceseseseseseseseseseseseseseseeeeees 2 11 2 7 6 eet eroe tet eee cs teins eese 2 12 DIT ZES ERROR CODES aa e ete ede et 2 12 30 EXECUTIVE CONTROL AND CASE CONTROL SECTIONS 3 1 3 1 EXECUTIVE CONTROL SECTION ienesis dson stentit sered enhn e n nnn n nnn nnn nnne a apap ies 3 2 3 2 CASE CONTROL SEGTION ee Perte ree eee e Eee ee Ope eye ee ee NET VENE 3 34 TABLE OF CONTENTS cont 4 0 5 0 6 0 7 0 Page ZONAIR BULK DATA SECTION eene 4 1 4 1 FORMAT OF BULK DATA CARDS ccccccecececececececececececececececececececececececececececececececececececececesecs 4 1 4 2 BULK DATA CARDS SUMMARY AND enne enne 4 4 4 2 1 AERODYNAMIC MODEL 4 5 4 2 2 SPLINE INPUT SPLINE 4 7 4 2 3 AERODYNAMIC ANALYSIS FOR COMPUTING THE PRESSURE AND FORCE MOMENT COEFFICIENTS 1 4 0 4 2 4 AEROHEATING
54. ATTACH Aerodynamic Panel To Structural Grid Spline Attachment Description Defines aerodynamic panel s to be attached to a reference structural grid for splining The ATTACH bulk data card is activated only if SSOLUTION 1 Executive Control Command is specified Format and Example 1 2 3 4 5 6 7 8 9 10 m m9 Field Contents EID Element identification number Integer gt 0 See Remark 2 MODEL NOT USED SETK Identification number of PANLST1 PANLST2 or PANLST3 bulk data card used to identify the aerodynamic panel ID s Integer gt 0 REFGRID Reference structural grid point identification number Integer gt 0 See Remark 3 Remarks 1 ATTACH is used only for computing the flexible loads For an aerodynamic component not represented in the structural model ATTACH is used to translate the displacements and loads between a structural grid point and the aerodynamic component A typical example is an underwing store that is modeled structurally by a concentrated mass at a single structural grid point In this case the respective aerodynamic model of the underwing store will be splined to this single structural grid point by ATTACH The resulting motion on the aerodynamic panels will be a rigid body motion that follows the motion of this single structural grid point 2 EID is used only for error messages 3 The translational and rotational degrees of freedom at the referenc
55. C by the FJKS000 PIN io p RM Kset x Jset and following equation where Complex DJKS000i Cp 4u000i F KSs 000 00017 x Kset 6 x Jset Same as 5000 and 015000 but for the anti Kset x Jset n an where omplex DiKAooo Symmetrie Kset 6 Jset Spline matrix relates 6 d o f structural displacement at structural grid to aerodynamic boxes i e x UGTKG x where is the 6 d o f displacements at aerodynamic boxes is the 6 d o f displacements at structural grid Note that x has 6 d o f namely 7 and at each structural grid where r and are Gset x Kset the modal displacement along x y and z directions where UGTKG of the local coordinates and g are the modal Gset 6 x numbers Real 4 128 BULK DATA DESCRIPTION OUTPUT4 EN Symmetric matrix imported by the ASSIGN FEM T He where Hset Real Executive Control Command number of modes APHI Same as SPHI but for anti symmetric modes Gset Real Generalized symmetric mass matrix imported by the PMEH ASSIGN FEM Executive Control Command S Real AMMH Same as SMHH but for the anti symmetric structures Hset x Hset Real Generalized symmetric stiffness matrix imported by the ASSIGN Executive Control Command Real AKHH Same as SKHH but for the anti symmetric structures Hset Hset Rea
56. CBARs attached to the panel edges wihich are on the UPPER side of the wake sheet pom Two CBARs attached to the panel mu edges wihich are on the LOWER side of the wake sheet These CBAR s generate wake sheets that extend to infinity ensuring that the gap between the root of the wing wake and the body is filled up by the wake sheets 4 50 BULK DATA DESCRIPTION CAERO7 wake from wing Noted that these internally generated CBAR elements can be individually removed This is done by specifying negative identification numbers of two consecutive grids that are listed the SET1 bulk data card including the trailing edge grid referred to by the LRCHD LTCHD entry This internally generated CBAR element between these two grids will be consequently removed by the program XRL YRL ZRL XTL YTL and ZTL implicitly define the normal vector of the CAERO7 macroelement This normal vector is computed by the cross product between the vector from leading to trailing edge and the vector from XRL YRL ZRL to XTL YTL ZTL Noted the upper surface of the CAERO7 macroelement is also defined by this normal vector BULK DATA DESCRIPTION 4 51 CAEROCP CAEROCP Apply a factor to the pressure coefficients on the CAERO7 macroelements Description Apply a factor to the pressure coefficients on the upper and lower surface of a CAERO7 macroelements Format and Example 1 2 3 4 5 6 7 8
57. CTRIA3 s and CQUAD4 s define the connectivity between the grids e Only the starting lines of the wake need to be defined via CBAR elements There are no input requirements for the surface wake PATRAN I DEAS etc can be employed directly for pre and post processing The entire configuration is first divided into several networks Each network is further divided by m x n set of grids Matching of doublet singularity between adjacent networks requires additional input e The location of the wake surfaces must be explicitly modeled No commercially off shelf software can be used directly for pre and post processing Figure 1 7 Comparison of ZONAIR and PANAIR Paneling Schemes on Random Panels Figure 1 8 Regular and Random Paneling of a Sphere at M 0 0 and a 0 0 deg 1 6 In what follows some validation cases for ZONAIR aerodynamics ranging from subsonic to hypersonic as well as multi body interference wave drag predictions ground effects aeroheating analysis and wake relaxation are shown Subsonic Aerodynamics VALIDATION CASES FOR ZONAIR AERODYNAMICS RM L51F07 wing body configuration at M 0 6 a 4 e Pressures along the body show strong wing body interference e Good correlation with the wind tunnel measurements INTRODUCTION HH Lj HH 2 2 2 2 22 HHF 72 ZH 7 7 77 2 7 A 1
58. Character or Real See Remark 6 Two options are available Characters FREE The value of the trim variable is an unknown and to be solved by the trim system Real Value The value of the trim variable is fixed and given by the real value BULK DATA DESCRIPTION 4 179 TRIM Remarks 1 For the static aeroelastic trim analysis the TRIM discipline must be selected the Case Control Section with TRIM TRIMID Note To compute the distributed inertial loads of a free free structure i e with rigid body vibration modes it is required to specify the rigid body d o f in the SUPORT entry of the ASSIGN FEM Executive Control Command import the SMGH from symmetric asymmetric finite element modal analysis or and the AMGH from anti symmetric modal analysis matrices by the ASSIGN MATRIX Executive Control Command The aerodynamics at the flight condition defined by the AEROGEN bulk data card are treated as the mean flow condition for the trim analysis For instance if ALPHA 10 0 degrees is specified in the AEROGEN bulk data card the values of all trim variables are treated as perturbed values about the 10 degrees mean angle of attack The units of the dynamic pressure must be consistent with the mass and length units specified in the FMMUNIT and FMLUNIT entries of the AEROZ bulk data card In fact all mass and length units involved in the TRIM bulk data card must be consistent with FMMUNIT and
59. Character or blank Character string either IPS TPS or BEAM to indicate a spline method for interpolating the wind tunnel measured pressure coefficient onto the ZONAIR panels For METHOD IPS the infinite spline method similar to the SPLINE1 bulk data card is used For METHOD TPS the thin plate method similar to the SPLINE3 bulk data card For METHOD BEAM the beam spline method similar to the SPLINE2 bulk data card is used Character See Remark 5 Identification number of a CORD2R bulk data card to define a local coordinate system For METHOD IPS the x y plane of the local coordinate system is the spline plane for the infinite spline method For METHOD TPS is not used For METHOD BEAM the y axis of the local coordinate system is the spline axis of the beam spline method Integer Identification number of a PANLST2 or PANLST3 bulk data card to list the identification numbers of the aerodynamic panels for spline Note that the PANLST1 bulk data card is not allowed Integer gt 0 Identification number of a SET1 bulk data card to list the identification numbers of the wind tunnel pressure points from which the wind tunnel measured coefficients are mapped to those ZONAIR panels listed in SETK Integer gt 0 1 The CPSPLN bulk data card replaces the ZONAIR computed pressure coefficients on the rigid aircraft by the wind tunnel measured pressure coefficients These pressure coefficients
60. Contents IDMK The identification number of a AEROGEN bulk data card whose generated AIC matrix is to be corrected Integer gt 0 See Remark 1 SYM Character string either SYMM ASYM or ANTI to specify the symmetric condition of the AIC matrix that is to be corrected by the downwash weighting matrix Character SYM SYM for symmetric condition SYM for antisymmetric condition SYM ASYM for asymmetric condition TYPE Character string to specify the type of the mode that is used to generate the given pressure coefficients Character Default RIGID See Remark 2 TYPE FEM The structural finite element modes that are imported by the ASSIGN FEM Executive Control Command TYPE AESURFZ The control surface modes that are defined by the AESURFZ AESLINK PZTMODE or GRIDFRC bulk data cards TYPE LOADMOD The load modes that are defined by the LOADMOD bulk data cards TYPE RIGID For rigid body modes 4 220 DATA DESCRIPTION WT2AJJ LABEL KINDEX METHOD WT2FILE FORM 1 INPCFDI A2 INPCFD2 PLTCP CPFILE Defines the index of the modes For TYPE FEM If LABEL is an integer LABEL represents the index of the structural finite element modes Integer gt 0 For TYPE AESURFZ LABEL represents the LABEL entry of the AESURFZ AESLINK or PZTMODE bulk data cards Character For TYPE LOADMOD If LABEL is an integer
61. FLEXLD bulk data card flexiblizes these rigid aerodynamic loads by including the structural flexibility effects 3 The units of the dynamic pressure must be consistent with the mass and length units defined in the AEROZ bulk data card 4 This OUTPUTA matrix can be imported back to ZONAIR using the INPDMI bulk data card 4 86 BULK DATA DESCRIPTION FLOWPT FLOWPT Aerodynamic Solutions at Flowfield Points Description Defines a set of points in the flowfield where the aerodynamic solutions are calculated Format and Example 1 2 3 4 5 6 7 8 9 10 FLOWPT IDFLOW IDAERO FORM INPFILE OUTFILE Fora Field Contents IDFLOW Identification number Integer gt 0 See Remark 1 IDAERO Identification number of an AEROGEN bulk data card Integer gt 0 See Remark 2 FORM FORM indicates the format of the flowfield point mesh on the external file Character Optional Default TECPLOT P3D Mesh is in the formatted PLOT3D format without IBLANK IP3D Mesh is in the formatted PLOT3D format with IBLANK UP3D Mesh is in the unformatted PLOT3D format without IBLANK and in single precision UDP3D Mesh is in the unformatted PLOT3D format without IBLANK and in double precision IUP3D Same as but with IBLANK IUDP3D Same as UDP3D but with IBLANK See Remark 3 NASTRAN Mesh is in the NASTRAN format See Remark 4 FREE Mesh is in the free format See Remark 5 TECPLOT Mesh is in the TECPLOT format See Remark 6
62. FMLUNIT respectively WEIGHT IXX IYY are multiplied by WTMASS to convert weight to mass These values define a 6x6 rigid body mass matrix such as WEIGHT WEIGHT WEIGHT IXX IXY IXZ IXY IYY IYZ IYZ IZZ It should be noted that WEIGHT IXX IYY must account for two sides of aircraft even if only half of the configuration XZSYM YES in the AEROZ bulk data card is modeled Also unlike the conventional definition the coupling terms IXY IXZ and IYZ have NO negative sign in the above matrix If NX NY NZ PDOT QDOT and or then its associated degree of freedom of the 6 rigid body motions three translational and three rotational degrees of freedom is eliminated from the trim system The remaining degrees of freedom are defined as trim degrees of freedom of the trim system Among these trim degrees of freedom if FREE is specified then the associated degrees of freedom are defined as free trim degrees of freedom real values are given the associated trim degrees of freedom are defined as given trim degrees of freedom If FREE is specified the trim variable is defined as free trim variable If real value is given the trim variable 15 defined as given trim variable The number of free trim degrees of freedom plus the number of free trim variables are the total number of unknowns of the trim system If the total number of unknowns of the trim system is equal to t
63. Hd 2 NC 1 ND 2 and Ais a real double precision array Double 3 NC 2 ND 1 and A is a complex single precision array Precision 4 NC 2 ND 2 and A is a complex double precision array Record 2 is repeated for each column At the end of the file Record 2 with the last column number plus 1 and at least one dummy value in A must be included Thus the total number of Record 2 in the file is NCOL 1 Remarks Remark 1 of ASSIGN MATRIX A single continuation line can be used in the ASSIGN MATRIX executive command control if the first line ends a comma 3 26 EXECUTIVE CONTROL SECTION CEND CEND The End of Executive Control Section Description Designates the end of the Executive Control Section Format CEND Example CEND Remarks CEND must exist at the end the Executive Control Section EXECUTIVE CONTROL SECTION 3 27 DIAG DIAG Diagnostic Output Options Description Request diagnostic output on special options Format DIAG K Ko Ki Example 1 DIAG 1 Example 2 DIAG 1 3 Describer Meaning Ki A list separated by commas of desired diagnostic Remarks 1 The DIAG command is optional 2 Multiple DIAG commands are allowed 3 The following are the possible values for K and their corresponding actions Turn on dynamic memory allocation debugger K 2 Print out the dynamic memor
64. IDVAR LABEL LOWER UPPER TRIMLNK INITIAL CONT Field Contents IDVAR Unique identification number Integer gt 0 See Remark 1 LABEL Character string to define the trim variable Character cannot be blank See Remark 2 LOWER The lower limit of the trim variable Active only for the over determined trim system Real Default 1 0 x 10 UPPER The upper limit of the trim variable Active only for the over determined trim system Real Default 1 0 x 10 See Remark 3 Note UPPER must be greater than LOWER TRIMLNK Identification number of a TRIMLNK bulk data card for trim variable linking Integer 2 0 See Remark 4 DMI Optional input to replace the program computed derivative of the pressure coefficients on the rigid aircraft with respect to the trim variable by the user supplied values If DMI is a character string this character string is the NAME entry of a DMI bulk data card or MNAME entry of an ASSIGN MATRIX Executive Control Command that contains the user supplied dC d trim variable If DMI is an integer this integer is the identification number of a TRIMINP bulk data card that defines the user supplied dC d trim variable Character integer or Blank See Remark 5 SYM Character string to define the types of the aerodynamic stability derivative generated by the trim variable Character See Remark 6 SYM SYM for longitudinal stability derivative SYM ANTI for lateral stabili
65. L Card Set 4 RVG j k iiz1 IMAX L j 1 JMAX L k 1 KMAX L UTE RW IMAX L j 1 JMAX L k 1 KMAX L 1 1 IMAX L j 1 JMAX L k 1 KMAX L RHO ij k Non dimensionalized density Real or Double RU i j k Non dimensionalized momentum along x precision RV k Non dimensionalized momentum along y RWh i k Non dimensionalized momentum along z 1 Non dimensionalized total energy per unit volume Repeat Card Sets 2 and 3 NBLK times L L l Note that FMACH and ALPHA must match the Mach number and angle of attack specified in the AEROGEN and MACH bulk data cards Otherwise a warning message occurs 4 104 BULK DATA DESCRIPTION INPCFD1 Imports CFD Solution from an unstructured CFD Code Description Imports the steady mean flow solution by interpolating the Computational Fluid Dynamics CFD Solution computed at an unstructured mesh to the ZONAIR surfaces panel model Format and Example INPCFD1 IDCFD1 DATA CFDFILE NORMCFD XSCALE Ear INPCFD1 10 PLOT3D CFDFILE DAT oem e J 1 Field Contents IDCFDI If IDCFD is a positive integer it refers to the identification number of an AEROGEN bulk data card The pressure coefficients at the flight condition defined by the AEROGEN bulk data card with ID IDCFD computed by the program are replaced by the CFD solution Integer If IDCFD is a negative integer
66. LABEL represents the identification number of the LOADMOD bulk data cards Integer gt 0 For TYPE RIGID LABEL is a character string and must be one of the following For SYM SYM LABEL FORAFT Represents the for aft translational mode LABEL PLUNGE Represents the plunging mode and LABEL PITCH Represents the pitching mode For SYM LABEL YTRANS Represents the y translational mode LABEL YAW Represents the yawing mode and LABEL ROLL Represents the rolling mode For SYM ASYM LABEL can be one of the character strings FORAFT PLUNGE PITCH YTRANS YAW or ROLL Character Default PITCH Not used Not used WT2FILE is a character sting representing the name of the output file that contain the computed downwash weighting matrix Character or Blank Character string either DMI or CFD to specify the form of the given pressure coefficients Character Multiplication factor to the pressure coefficients that are imported by the entry INPCFD1 Real See Remark 5 For FORM INPCFDI is a character string of the name of the matrix that is imported by the DMI bulk data card or an ASSIGN MATRIX Executive Control Command For FORM CFD INPCFDI is an integer that is the identification number of an INPCFD INPCFDI INPDMI CPSPLN bulk data card Character Integer or Blank Same as 1 but
67. MATRIX Executive Control Command for a group of elements Note If LABEL DMI or PCHFILE is specified the TRIMFNC bulk data card can represent many trim functions The number of trim functions depends on the number of columns of the matrix For a symmetric configuration XZSYM YES in the AEROZ bulk data card ZONAIR requires only the modeling of half of the configuration For asymmetric trim system ZONAIR superimposes the results of the symmetric trim system and the anti symmetric trim system to obtain the results on both sides of the configuration The entry RHS is used only if LABEL or LOADMOD for TYPE AERO TYPE FEM and TYPE MODAL For asymmetric configuration XZSYM NO in AEROZ bulk data card RHS must be RHS Since all entries of the bulk data cards cannot have embedded blanks the blanks for separating words will lead to a fatal error For instance the description STRESS AT CBAR has embedded blanks which are not allowed To circumvent this problem it is recommended to use a period between the words such as STRESS AT CBAR BULK DATA DESCRIPTION 4 189 TRIMINP TRIMINP Imports Pressure Derivatives Description Replaces the program computed pressure derivatives of a trim variable by the user supplied values Format and Example 1 2 3 4 5 6 7 8 9 10 TRIMINP IDINP INPCFD1 INPCFD2 FORM FILENM rd Fiel
68. Method Description Defines a 3 D spline using the thin plate spline method The SPLINE3 bulk data card is active only if the SOLUTION 1 is specified Format and Example 1 2 3 4 5 6 7 8 9 10 Field EID MODEL CP SETK SETG DZ EPS Remarks Contents Unique element identification number Integer gt 0 Not used Not used The identification number of a PANLST1 PANLST2 PANLST3 bulk data card that lists the aerodynamic panel identification numbers Integer gt 0 Refers to SETi bulk data card that lists the structural grid points to which the spline is attached Integer gt 0 Not used Multiplication factor to obtain a small tolerance to detect any duplicated location of structural grid points The tolerance is computed by EPS REFC where REFC is the reference chord defined in the AEROZ bulk data card Real gt 0 0 Default 0 01 1 SPLINES3 employs the Thin Plate Spline TPS method Unlike the infinite plate spline method employed by the SPLINEI bulk data card the SPLINE3 does not require that a spline plane be defined structural grid points are located in 3 D space Therefore the TPS method can be considered as a 3D spline method 2 Two restrictions are associated with the 3D spline method a Similar to SPLINE1 no two or more structural points can be at the same location b of the structural points cannot be located in the same plane EPS is the tol
69. RFS SSO LUE E ASSIGN RUNDB DEMO NEW PASSWORD DEMO REALLOC io BO ae ts RE Ses 72045 26730 ts BF ote vu S SB OL eR 46055 QE LSQ70SS XX 259055 SOLUTION CONTROL SUMMARY ANALYZE BOUNDARY METHOD 20 REDUCE 30 SPC 10 LABEL DEMO CASE MODES PRINT MODES ALL DISP ALL ROOT ALL END SORTED BULK DATA ECHO CARD COUNT ers deg Mig BE X wed EE ae De ER oh OL 1 ASET1 30 3 10201 THRU 10204 2 ASET1 30 3 10101 THRU 10104 5 30 3 10401 THRU 10404 4 ASET1 30 3 10301 THRU 10304 EXECUTIVE CONTROL SECTION 3 9 ASSIGN FEM 5 CBAR 1010 1010 10102 20000 10101 6 CONVERT MASS 00259 i CQUADA 1001 1000 10101 10102 10202 10201 So CQUAD4 1002 1000 10102 10103 10203 10202 ec CQUAD4 1003 1000 10103 10104 10204 10203 10 CQUAD4 1004 1000 10201 10202 10302 10301 11 CQUAD4 1005 1000 10202 10203 10303 10302 12 CQUADA 1006 1000 10203 10204 10304 10303 3 CQUAD4 1007 1000 10301 10302 10402 10401 14 CQUAD4 1008 1000 10302 10303 10403 10402 Tbs CQUAD4 1009 1000 10303 10304 10404 10403 16 EIGR 20 MGIV 500 0 5 ABC TT ABC MAX 18 GRID 10101 0 0 30 000 0 0 19 GRID 10102 33 333 30 000 0 0 20 GRID 10103 66 667 30 000 0 0 21 GRID 10104 100 000 30 000 0 0 22 GRID 10201 16 667 53 333 0 0 23 GRID 10202 44 444 53 333 0 0 24 GRID 10203 72 222 53 333 0 0 25 GRID 10204 100 000 53 333 0 0 26 GRID 10301 33 333 76 667 0 0 27 GRID 10302 55 555 76 667 0 0 28 G
70. Remarks 1 The GENBASE Case Control Command must appear within a subcase section i e between two subcase control commands 2 The integer N is the identification number of a GENBASE bulk data card Integer gt 0 This GENBASE bulk data card refers to a number of AEROGEN bulk data cards whose computed aerodynamic force and moment coefficients are exported to an external file 3 GENBASE and N must be separated by an equals sign 3 38 CASE CONTROL SECTION LABEL LABEL Provides Additional Description of a Subcase Description Provides additional description of a subcase by a character string up to 72 characters in length Format LABEL Example LABEL This is a test case Remarks 1 The LABEL Case Control Command must appear within a subcase section 2 A represents a character string up to 72 characters in length that allows for additional description of the subcase within which the LABEL Case Control Command is located 3 Within each subcase section only one LABEL Case Control Command is allowed 4 Ifno LABEL exists in a subcase section then the character string A is blank CASE CONTROL SECTION 3 39 SUBCASE SUBCASE Delimits and Identify a Subcase Section Description To start a subcase section and assign an identification number to the subcase Format SUBCASE n Example SUBCASE 2 Remarks 1 The Case Control Section can contain many subcase sections Each
71. Results File is used with four data quantities specified Steps within PATRAN to View the Aerodynamic Model with Pressure and Local Mach Numbers ZONAIR output file generated by PLTCP bulk data card Open a new PATRAN database Read in the geometry file first Select File Import from the Radio buttons Object Model Source Neutral select the appropriate geometry neutral file and click Apply PLOT FILES 7 9 Read in the pressure results file next Select File Import from the Radio buttons Object Results Source Patran2 els After selecting the Patran2 els locate the ZONAIR pressure results file in whatever directory it has been stored in Select the appropriate pressure results file and click Apply Verify that the import read was successful in the Dialog Box Select Results from the Radio buttons Action Create Object Quickplot The Fringe results list should show up results that were read in Select the desired pressure quantity and click Apply The following PATRAN results template can be used to load the pressures from ZONAIR ZONAIR pres res tmpl PATRAN 2 5 results file template for ZONAIR els files KEYLOC 0 TYPE scalar COLUMN 1 PRI Pressure Coefficient SEC Real TYPE scalar COLUMN 2 PRI Local Mach SEC Imag TYPE END e Tecplot Compatible Output A sample of the Tecplot output is shown in the following figure and is described below TITLE UNSTEADY CP
72. Rotate pan or autocenter the model with the Dynamic Rotate function top left button on the toolbar Node Point and Element features such as id s can be set in the View Options window NASTRAN Compatible Output The NASTRAN compatible output is saved in standard NASTRAN bulk data format NASTRAN compatible output is shown in the following figure and is described below BEGIN BULK GRID GRID GRID GRID GRID GRID CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 GRID GRID GRID GRID GRID ENDDATA AERO MODEL BY WHERE THE PSHELL ENTRES OF CQUAD4 ARE CAERO7 AND BODY7 IDENTIFICATION NUMBERS ADDITIONAL 201 202 203 204 205 206 201 202 203 204 205 206 10101 10102 10103 10104 10201 91 GRIDS AND 65 CQUAD4 17 FEM GRIDS ARE DISPLAYED 201 201 201 201 201 201 sb ex TS R8 0 3 6 T 1 202 203 204 205 207 208 0 00 020 00 020 00 020 00 020 00 020 00 010 000 000 000 000 000 000 000 000 000 000 000 00 207 208 209 210 212 213 000 010 000 010 000 010 000 010 333 010 000 00 000 00 000 00 000 00 000 00 1 70 01 206 207 208 209 211 212 000 00 000 00 000 00 000 00 000 00 Aerodynamic Grid Points 201 202 203 Quadrilateral 204 Elements 206 207 THE FOLLOWING GRIDS ARE THE FEM GRIDS IN THE AERODYNAMIC COORDNATES 1DS ARE OFFSET BY BASIC ON ACSID IN THE AEROZ BULK DATA ENTRY 000 003
73. SECTION ASSIGN FEM ASSIGN FEM Structural Modal Data Importer Description Assigns an external file that contains the free vibration solutions of the finite element model for static aeroelastic analysis by specifying the SOL Executive Control Command as SOL 1 Format ASSIGN FEM a FORM b BOUNDARY c PRINT n SUPORT m L Example 1 ASSIGN FEM demol f06 FORM MSC BOUNDARY SYM PRINT 1 SUPORT 123 Example 2 ASSIGN FEM export home ZONAIR demo2 f06 BOUNDARY ANTI SUPORT 246 3000 Describer Meaning FEM FEM indicates that a is the filename of the external file that contains the free vibration solution of the structural finite element model a isa character string specifying the name of the external file Required UNIX systems are case sensitive therefore lower upper case characters must identically match the name of the file DOS and WINDOWS systems are not case sensitive see Remarks 1 and 2 FORM b FORM indicates the name of the structural finite element code that generates the output file a by a free vibration analysis where b is a character string specifying the name of the structural finite element code Optional Seven options are available for b Data of the free vibration solution is MSC generated by MSC NASTRAN see Remark 3 UAI generated by UAI NASTRAN see Remark 3 CSA generated by CSA NASTRAN see Remark 3
74. TEST 0 1 0 5 0 4 0 10 0 10 20 10 0 10 20 10 5 0 5 10 15 20 Angle of attack Angle of attack Angle of attack Hypersonic Aerodynamics Equivalent Mach number transformation to circumvent the superinclined panel problem Local pulsating body analogy for flow rotationality effects Good agreement between ZONAIR and CFL3D on the CKEM body at various bent nose angles at M 6 0 Undeflected Case Body amp Nose at the same AOA Nose Body 2 at M 6 0 lower CFL3D Cp upper CFL3D Cp lower ZONAIR Cp upper ZONAIR 5 10 15 20 25 30 35 40 CFL3D ZONAIR Positive 2 Deflection between Body amp Nose Nose 0 Body 2 at M 6 0 0 0465 H 0 050 0 00612 C 0 118 0 1125 0 0549 0 05588 0 00668 TTT Cp_lower CFL3D Op upper CFL3D lower ZONAIR Op upper ZONAIR 0 10 15 20 25 30 35 40 CFL3D ZONAIR 0 076 0 0712 Cy 0 02552 0 02776 Cp 0 0553 0 049 3 76 7 0 Positive 2 Deflection between Body amp Nose Nose 2 Body 05 at M 6 0 lower CFL3D Cp upper CFL3D lower ZONAIR Cp upper ZONAIR CFL3D
75. TRIMADD bulk data card The Von Mises stress formula is expressed as follows 2 2 214 x Oo 0 0 era where c c and 7 are the stresses of an element in the finite element mode and 4 4 and A are constants To construct the Von Mises stress formula by the TRIMADD bulk data card it is required first to specify three TRIMFNC bulk data cards which define three trim functions referring to and T stresses of an element respectively The identification numbers of these TRIMFNC cards for instance are ID ID and ID The entries of the TRIMADD bulk data card are for the term _ A A S L I 10 SYMBOL s l 6 10 E 10 A 4 for the term z SYMBOL 5 21 E ID C 2 0 E 210 A for the term SYMBOL s 1 R Ij G 20 E 10 A D for the term Ej 5 SYMBOL s L F 51D G 226 A 4 and finally 0 5 BULK DATA DESCRIPTION 4 183 TRIMCON TRIMCON Constraint Functions for the Static Aeroelastic Trim Analysis Description Defines a set of constraint functions to be satisfied for solving the over determined trim system G is defined as G ES c where F represents the value of a trim function Format and Example Pee E EET Field Contents IDCONS Unique identification number Integer gt 0 See Remark 1 IDFNC Identification number of a TRIMFNC or TRIMADD bulk data card whose value i
76. The existence of each PLTSURF in the bulk data input triggers the generation of a data file for the purpose of plotting the deflected control surface on the aerodynamic model SETID is used for error message output only The control surface is deflected about its hinge line with a unit deflection angle The format of the data file is defined by the FORM entry The control surface deflection data are added to the x y and z values of the aerodynamic grids to create a deformed aerodynamic model Using the TECPLOT or PATRAN software depends on FORM TECPLOT or PATRAN the deformed aerodynamic model can be displayed graphically For I DEAS universal file output data sets 781 and 780 are used for displaying the aerodynamic grids and boxes respectively A data set 55 1s used to output the six degree of freedom displacements at all aerodynamic grid For FEMAP neutral file format Data Blocks 403 and 404 are used for displaying the aerodynamic grids and boxes respectively Data Block 45 is used for displaying the deformed mode shape TOTAL Translation X axis translation T1 Y axis translation T2 and Z axis translation T3 The interpolated mode shape can either be statically deformed or animated The ANSYS output is a FEMAP neutral file that can be read in by an ANSYS neutral file translator developed by PADT Inc PATRAN requires that the aerodynamic model be stored in a neutral file and that analysis results be stored in a results fi
77. The identification number of the LOADMOD bulk data card is defined in the ISSET entry of the TRIMFNC bulk data card See Remark 2 For TYPE FEM LABEL can either be LOADMOD LOADMOD1 GRIDDISP or FORCE Characters LOADMOD Description The component loads due to the aerodynamic loads and inertial loads at a set of structural finite element grid points that are specified in the SETG entry of the LOADMOD bulk data card is defined as the trim function identification number of the LOADMOD bulk data card is defined in the ISSET entry of the TRIMFNC bulk data card See Remark 2 LOADMODI Same as LABEL LOADMOD except the aerodynamic component loads are obtained by integrating the aerodynamic pressure over those aerodynamic boxes defined by the SETK entry of the LOADMOD bulk data card Note that for LABEL LOADMOD the aerodynamic forces are first transferred from the aerodynamic grids to the structural grids using the spline matrix Then the aerodynamic component loads are obtained by integrating the aerodynamic forces at those structural grids defined by the SETG entry of the LOADMOD bulk data card Because of the force transferral using the spline matrix the conservation of forces is not always ensured On the other hand for LABEL LOADMODI because there is no force transferral involved it gives the most accurate results of the component loads GRIDDISP The disp
78. UNIX Script File Process described earlier except step 6 as follows 6 Establish a run time database folder 1 directory using the first available 1 lowest number folder to obtain a new folder extension For example if two jobs were already submitted that occupy folders ZONAIRO001 and ZONAIRO04 and a third job is to be submitted then a folder name of ZONAIROO2 would be used Note that up to 999 jobs can be submitted at one time on the PC system Run time Database Directory The ZONAIR software system run time database directory location is specified in the file DIRNAME FIX which is set up upon installation of the software Folders i e directories are set up under this location for each job submitted via the ZONAIR script file as described earlier in this section Upon normal termination of a job the run time database folder is deleted except under the following conditions ifthe computer is shutdown or if power failure occurs during execution of a job ifa ZONAIR script file job is terminated by the user e g by closing MS DOS prompt window or is terminated by some other means e g by the Windows operating system In such situations the run time database folders are left in the run time database directory and can occupy tremendous amounts of disk space Therefore the user should manually remove any run time database folders of jobs that are no longer running How TORUNZONAIR 2 9 2 7
79. XZSYM YES in the AEROZ bulk data card only modeling half of the configuration is required even for a vertical tail whose mean plane is located on the X Z plane This is to say that because of the absence of the left hand side surface of the vertical tail surface it is not required to generate the CQUAD4 CTRIA3 and CROD elements in the left hand side of the model In this case UPSETI 0 or LOWSET1 0 is required where the specification of UPSETI 0 or LOWSETI 0 determines the normal vector of those CQUAD4 CTRIA3 on the right hand side of the model See Remark 3 BULK DATA DESCRIPTION 4 37 AUTPVOR AUTOVOR Automatically Generates a VORNET Macroelement Description Automatically generates a VORNET bulk data card to model a vortex roll up sheet for nonlinear lift at high angles of attack Format and Example 1 2 3 4 5 6 7 8 9 10 AUTOVOR EID LABEL TIPGRID ANGLE CANT ROOLUP NFED CBAR CONT CONT GRID1 GRID2 GRID3 52 5 etc AUTOVOR 100 ROLLUP 101 10 1 30 0 CIRCLE 3 NO A A AUTO 100 200 Field Contents EID Unique identification number Integer gt 0 See Remark 1 LABEL An arbitrary character string used to define a label for the vortex roll up surface Character TIPGRID Identification number of a surface grid point where the roll up vortex starts Note that TIPGRID can be a negative integer This gives the generation of the roll up vo
80. a ZONAIR job is submitted the ZLS is contacted for checkout of a token With a successful checkout i e tokens available for the requested modules in the ZONAIR job a token file is saved under ZLS log directory the ZLS adjusts the token count and then the ZONAIR job proceeds After the ZONAIR job is finished the ZLS is contacted for a checkin With a successful checkin the token file is deleted and the ZLS adjusts the token count accordingly In the event of an abnormal ZONAIR termination e g a power failure during a job token s can become locked To release locked token s a cleanup utility is provided The utility program zonair cleanup exe or zonair cleanup for Unix or Linux can be found in the ZONAIR home directory under the ZLS log directory To run the cleanup utility open a command prompt window UNIX and Linux or an MS DOS prompt window Windows change the directory to ZONAIR home directory ZLSMog and type zonair cleanup When executing zonair cleanup if a locked token is found you will be prompted whether you wish to release the token back to the ZLS Token file names are in the format of log nnn DD MMM Y Y hh mm ss e g log 001 14 MA Y 09 17 22 14 The time stamp in the log file name shows submission time of ZONAIR job and nnn indicates its tmp directory Therefore token file names can be used to judge if corresponding tokens should be freed while running zonair cleanup Instead of using cleanup utility to release
81. a given axial station 1 Body of Revolution using ITYPEi 1 and Xi CAMi entries 2 Elliptical Body using ITYPEi 2 and Xi YRi ZRi entries 3 Arbitrary Body using ITYPEi 3 and Xi IDYi IDZi entries Body centerline defined by the iind of Revolution x axis specified inthe ACOORD 5 LU q bulk data entry CAM NAXIS BULK DATA DESCRIPTION 4 43 BODY7 Elliptical Body Arbitrary Body Z Low 3 For a body of revolution or elliptical body the number of circumferential points are divided evenly for the body If YORIGN defined in the ACOORD bulk data card to which the body refers is zero and the XZSYM entry of the AEROZ bulk data card is YES only half of the body on the positive Y side is generated Conversely if YORIGN is not zero and the XZSYM entry of the AEROZ bulk data card is YES the points must be distributed over the entire circumference of the body e g an underwing store For this case the first and last points are coincident points See figures below However if the XZSYM entry of the AEROZ bulk data card is NO then the entire body must be input 1 all circumferential points defined regardless of the value of YORIGN 2 2 YOBIGN 0 YORIGN 0 Y Y NRAD 9 NRAD 9 Two Coincident grids For an arbitrary body the circumferential points must be entered in a counterclockwise direction as viewed along the negative x axis looking at the y z plane in local body c
82. a negative integer in this case TRANSF 50 to flip the CFD mesh from the negative y axis to the positive y axis 4 102 BULK DATA DESCRIPTION INPCFD 3 Because ZONAIR only requires the CFD solution on the surface mesh to replace the program computed pressure coefficients by those computed by CFD specifying the CFD surface mesh index can avoid the reading of all CFD mesh into the computer memory 4 Big endian and little endian are two ways of representing data format Little endian stores data with increasing numeric significance in increasing memory addresses By contrast big endian stores data with increasing numeric significance in decreasing memory addresses x86 processors adopt little endian format Little endian systems include PC Windows big endian systems include SGI and HP 5 The CFD mesh must be in the PLOT3D format For the formatted file all data are written in the free format For the unformatted file all data are stored in the binary format The PLOT3D format is shown as follows Card Set 1 NBLK NBLK Number of blocks of the CFD mesh Integer gt 0 Example 2 Card Set 2 IMAX L JMAX L KMAX L L 1 NBLK IMAX L IMAX JMAX and KMAX are the number of grid points along the I J and JMAX L K directions of each block respectively Integer gt 0 KMAX L L 1 If FORMCFD P3D UP3D or UDP3D Card Set 3 1 1 IMA X L j 1 JMAX L
83. all PANLST2 with the same SETID are included in the set For instance the following two PANLST2 bulk data cards with the same SETID 10 yield 5 aerodynamic panels with identification numbers of 1 2 3 25 and 104 respectively 4 134 DATA DESCRIPTION PANLST3 PANLSTS3 Set of Aerodynamic Panels Description Defines a set of aerodynamic panels by the LABEL entry in CAERO7 BODYT or the MATBODY bulk data cards Format and Example 1 2 3 4 5 6 7 8 9 10 Field Contents SETID Unique set identification number Integer gt 0 See Remark 1 LABELi Character string that matches the entry LABEL in the CAERO7 BODY7 or MATBODY bulk data cards Character See Remark 2 Remarks 1 PANLSTS is referred to by SPLINEi ATTACH LOADMOD JETFRC and or AESURFZ bulk data card 2 All aerodynamic panels of the CAERO7 or BODY7 macroelement with LABEL defined in the CAERO7 or BODY7 bulk data card as well as all CQUAD4 CTRIA3 panels referred to by the MATBODY bulk data card are included in the set Note If PANLST3 is referred to by the SPLINE1 bulk data card only one LABEL entry is allowed BULK DATA DESCRIPTION 4 135 PARAM PARAM Description Values of Parameters Alters values for parameters used in the computation Format and Example 1 2 3 4 5 6 7 8 9 10 Field NAME VALUE Remarks Parameter name Character Contents Parameter valued based on the parameter typ
84. and internally adds another set of grid points In fact GRIDi are the entry GRIDUi and those internally generated grid points are the entry GRIDLi of the VORNET bulk data card Note that the last GRIDi can be a negative integer In this case the last GRIDi will not be sliced into two grid points If GRID is the character string AUTO all downstream grid points from TIPGRID to the end of the body or the trailing edge of the wing can be automatically identified by the program Thus all the rest of GRIDi is not required for input However if GRID 0 then it is the identification number of a surface grid that is used to define an initial search vector for the identification of the downstream grid points This vector starts from TIPGRID and towards GRID If GRID 0 the x axis is used as the initial search vector If GRID 0 it is the identification number of a surface grid point at which the vortex roll up sheet ends If GRID 0 the vortex roll up sheet automatically ends at the end of a body or the trailing edge of a wing Note that GRID can be a negative integer In this case the search vector does not slice the grid point with ID GRID into two grid points Integer or Character see Remark 3 Remarks 1 The AUTOVOR bulk data card internally generates a VORNET bulk data card by automatically setting up all entries in the VORNET bulk data card The identification number of this internally generated VORNET bulk data card is
85. axis Integer See Remark 2 FILEWT File name to specify an ASCII file where the wind tunnel measured pressure coefficients are stored If the first character of FILEWT starts with a dollar sign the rest of the characters must be integers This integer is the identification number of an EXTFILE bulk data card where the filename is specified The feature allows for filenames up to 72 characters to be input Character Z blank See Remark 3 4 66 BULK DATA DESCRIPTION CPSPLN FORM PLTFILE METHOD SETK SETG Remarks The format of the output plot file PLTFILE FORM TECPLOT for generating a TECPLOT file FORM PATRAN for generating a PATRAN neutral file FORM IDEAS for generating an I DEAS universal file FORM FEMAP for generating a FEMAP neutral file FORM ANSYS for generating an ANSYS supported neutral file FORM for generating a NASTRAN bulk data deck Character default TECPLOT See Remark 4 File name to store the wind tunnel measurement locations and the ZONAIR aerodynamic panel model together to verify the overlapping between these two models If the first character of PLTFILE starts with a dollar sign the rest of the characters must be integers This integer is the identification number of an EXTFILE bulk data card where the filename is specified The feature allows for filenames up to 72 characters to be input
86. by the UGFRC matrix but it may result a in a poor distribution of forces if the structural grid points involved in the force spline are not carefully selected BULK DATA DESCRIPTION 4 169 SPLINEM SPLINEM Save or Retrieve the Spline Matrix Description Saves the spline matrix on an external file for the cold start job or retrieves the spline matrix from the external file for the restart job The SPLINEM bulk data card is active only if the SOLUTION 1 Executive Control Command is specified Format and Example 1 2 3 4 5 6 y 8 9 10 oe se TIE EE Field Contents SAVE Character string either SAVE or ACQUIRE For SAVE SAVE save the spline matrix on the file FILENM For SAVE ACQUIRE retrieve the spline matrix from the file FILENM Character See Remark 1 FILENM File name to specify the file name on which the spline matrix 1s saved or retrieved If the first character of FILENM starts with a dollar sign the rest of the characters must be integers This integer is the identification number of an EXTFILE bulk data card where the filename is specified This feature allows for filenames up to 72 characters to be input Character See Remark 2 Remarks 4 The SPLINEM bulk data card is not referred to by any other bulk data card Its existence in the input file triggers the program to save retrieve the spline matrix Computation of the spline matrix for a large nu
87. card is active only if the SOLUTION 1 Executive Control Command 1s specified Format and Example T 2 3 4 5 6 7 8 9 10 Field Contents EID Unique element identification number Integer gt 0 See Remark 1 MODEL Not used SETK The identification number of a PANLST1 PANLST2 or PANLST3 bulk data card that lists the aerodynamic box identification numbers Integer gt 0 SETG The identification number of a SETi bulk data card that lists the structural grid points to which the spline is attached Integer gt 0 DZ Linear attachment flexibility Real gt 0 0 EPS Multiplication factor to obtain a small tolerance to detect any duplicated location of structural grid points The tolerance is computed by EPS REFC where REFC is the reference chord defined in the AEROZ bulk data card Real 0 0 Default 0 01 CID Rectangular coordinate system CORD2R bulk data card whose Y axis defines the spline axis i e the line of the beam Integer gt 0 or blank not used for BODY7 See Remark 2 CURV Curvature effects of the torsion stiffness Real 2 0 0 Default 1 0 See Remark 3 Remarks 1 Unlike SPLINE1 and SPLINES that require only the transitional degrees of freedom d o f of the structural grid the beam spline method also requires the rotational d o f for both accurate displacement and slope spline at the aerodynamic boxes Therefore the user must ensure that the structural grid defined by entry SETG have no unwa
88. commands The user must ensure that the structural finite element analysis is a free vibration analysis or normal modes analysis For MSC NASTRAN the solution sequence SOL 103 must be selected In addition the solution set eigenvector output SVECTOR ALL must not be selected Remark 4 of ASSIGN FEM A single continuation line can be used in the ASSIGN FEM Executive Control Command if the first line ends in a comma MSC NASTRAN Example The following figure shows a plate type of finite element model 10401 10402 10403 10304 10404 3 6 EXECUTIVE CONTROL SECTION ASSIGN FEM The MSC NASTRAN output file for normal modes analysis of the above model is listed as follows o NASTRAN SOL 103 CEND CARD COUNT CARD COUNT p 3 4 5 6 7 8 9 10 il 12 13 14 15 16 a 18 a9 20 21 22 23 24 25 26 27 28 29 30 315 32 33 34 305 36 37 38 39 40 41 42 EXECUT ECHO SORTED DISP ALL METHOD 20 SPC 10 BEGIN BULK IVE CONTROL CASE ECHO CONTROL INPUT BULK DATA CARD COUNT ASET1 ASET1 ASET1 ASET1 CBAR CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 CQUAD4 EIGRL GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID GRID 1 PARAM PARAM PBAR PSHELL SPC1 SPC1 SPC1 SPC1 SPC1 ENDDATA TO
89. coordinates Numerical experience shows that for a complete aircraft structure using the first fifty lower order modes for PHG is sufficient to achieve a converged solution The modal approach reduces the size of the trim system from over thousands degrees of freedom for a complete aircraft structure the number of degrees of freedom in the structural finite element model can easily be in the thousands down to as low as fifty Thus the modal approach offers a solution technique that is much more efficient than the direct method NASTRAN is only capable of solving the determined trim system the number of unknowns equal to the number of trim degrees of freedom In addition to the determined trim system ZONAIR can also solve the over determined trim system 1 e where the number of unknowns is greater than the number of trim degrees of freedom by using a feasible direction technique that minimizes a user defined objective function while satisfying a set of constraint functions The objective and constraint functions can be specified in terms of the so called trim functions that include induced drag component loads element stresses lower and upper limits of the trim variables etc For the asymmetric flight condition NASTRAN requires modeling of the whole aircraft both structurally and aerodynamically even if the configuration is symmetric about its mid plane By contrast for a symmetric configuration ZONAIR only requires modeling of
90. data card used to specify the x coordinate locations in percentage of the chord length where the thickness and camber are specified ITAX can be a negative number where ABS ITAX bulk data card identification number to request linear interpolation Integer See Remark 1 Identification number of an AEFACT bulk data card used to specify the half thickness of the airfoil at the wing root Integer 2 0 Identification number of an AEFACT bulk data card used to specify the camber of the airfoil at the wing root Note that the positive values are along the normal vector of the CAERO7 macroelement See remark 7 of the bulk data card Integer gt 0 Leading edge radius at the root normalized by the root chord Real 2 0 0 Identification number of an AEFACT bulk data card used to specify the thickness at the wing tip Integer 2 0 Identification number of an AEFACT bulk data card used to specify the camber at the wing tip Integer 2 0 Leading edge radius at the tip by the tip chord Real 2 0 0 1 x coordinate values listed in the AEFACT bulk data card must start with 0 0 and end with 100 0 If ITAX is a positive integer then a cubic interpolation is used between the airfoil points established by the ITAX ITHR ICAMR RADR ICAMT and RADT entries However ITAX can bea negative number which implies that a linear interpolation is used between the airfoil points For example if the d
91. detectable by the program and may lead to incorrect results Some of these situations can be avoided by following the modeling guidelines presented in this section 5 1 AERODYNAMIC COORDINATE SYSTEM The aerodynamic coordinate system is the basic coordinate system in which the entire aerodynamic model geometry is defined Since ZONAIR solves the small disturbance potential equation 1 Moo Bex 0 0 5 1 where M is the freestream Mach number and is the velocity potential the compressible direction of the flow is inherently along the x axis of the aerodynamic coordinate system as shown in Figure 5 1 In addition if the configuration is symmetric about the x z plane as the one shown in Figure 5 2 only one half of the configuration located in the positive y axis region is required for modeling For the half model ZONAIR can automatically account for the aerodynamic influence between the half configuration located in the positive y axis and the negative y axis by a mirror image technique Compared to a full model this mirror image technique can reduce the size of the problem by a factor of two and save computational time Note that this symmetry condition is specified by the XZSYM entry of the AEROZ bulk data card GUIDELINES FOR AERODYNAMIC MODELING 5 1 Flow direction Figure 5 1 The Aerodynamic Basic Coordinate System Positive y region ZONAIR auto modeled left hand zn side of the configuration
92. each CQUAD4 panel into six sub triangular panels show below 4 70 BULK DATA DESCRIPTION CQUAD4 Gl G4 G2 G3 Two CQUAD4 sharing three grid points will give a coincidence of the sub triangular panels and lead to a singular matrix In the following figure two CQUAD4 share the same three grid points G and G3 In this case one can see that the third sub triangular panels of the upper and lower CQUAD4 panels coincide with each other To avoid such a coincidence one can use two CTRIA3 panels instead of one CQUAD4 panel G G Coincidence of sub triangular panels Using two CTRIA3 panels to avoid the coincidence of G sub triangular panels 2 BULK DATA DESCRIPTION 4 71 CROD CROD Line Vortex Element Description Defines a line vortex element by two surface grid points Format and Example i 2 3 4 5 6 7 8 9 10 CROD EID GRIDO GA GB CROD 1 101 141 105 Field Contents EID Identification number Integer gt 0 See Remark 1 GRIDO A surface grid ID at which this line vortex element originates Integer gt 0 GA GB Identification numbers of two GRID bulk data cards GA and GB must be the surface grid points PS 0 in the GRID bulk data card Integer gt 0 Remarks 1 Theline vortex element is usually placed along the tip of a thick wing component to simulate the tip vortex effects GRIDO CROD GB 2 The CROD genera
93. field 9 If there are more than 8 entries required for a bulk data card the so called continuation label is required in the tenth field and more than one input cards are needed The additional input cards are called continuation lines A typical example of this kind of bulk data card is shown as follows AEFACT SID D1 D2 D3 D4 D5 D6 D7 CONT CONT can be any alphanumeric string including blanks CONT D8 D9 etc 4 2 BULK DATA DESCRIPTION Example AEFACT 100 0 0 0 2 0 3 0 4 0 5 0 6 0 7 A A 0 8 0 9 There are several major differences between ZONAIR and NASTRAN regarding the treatment of continuation lines ZONAIR has the following restrictions e The continuation lines must follow their associated bulk data card No other bulk data cards can be inserted between continuation lines except a comment e If continuation label is blank no other bulk data cards can be inserted between continuation lines including a comment e Duplicate continuation labels may be used For example the following bulk data cards with continuation lines are acceptable Example 1 AEFACT 100 0 0 0 2 0 3 0 4 0 5 0 6 0 7 A A 0 8 0 9 1 0 121 1 2 1 3 1 4 1 5 A 1 6 Example 2 AEFACT 100 0 0 0 2 0 3 0 4 0 5 0 6 0 7 A A 0 8 0 9 1 0 1 1 1 2 1 3 1 4 1 5
94. for the pressure coefficients imported by the entry INPCFD2 Real Same as INPCFDI but for the second set of pressure coefficients Character string to specify the format of the plot file of CPFILE PLTCP TECPLOT for generating the TECPLOT file PLTCP PATRAN for generating the PATRAN neutral results file PLTCP IDEAS for generating the I DEAS universal file PLTCP FEMAP for generating the FEMAP neutral file PLTCP ANSYS for generating an ANSYS supported neutral file PLTCP NASTRAN for generating the NASTRAN bulk data deck with PLTCP cards to define the pressures loads PLTCP ESA for generating the PEGASUS readable file Character Default Character string up to 16 characters to specify the filename of a graphical file that contains the aerodynamic model and the ACp This allows the user to verify the computed ACP sven from the entries Al INPCFD1 2 and INPCFD2 Character or Blank BULK DATA DESCRIPTION 4 221 WT2AJJ Remarks 1 WT2AJ J bulk data card generates a downwash weighting matrix WT2 such that ACP nen 2 where ACP given is the given pressure coefficients that can be either computed by the CFD codes or measured by wind tunnel test AJJ is the so called uncorrected AIC matrix directly computed by the program WT2 is the downwash weighting matrix generated by the WT2AJJ bulk data card and W is the mode by whi
95. is automatically checked by the program for all surface grid points If this condition of any surface grid point is not satisfied fatal error occurs However this condition can be relaxed by specifying the PARAM bulk data card See description of the PARAM bulk data card with entry NAME GRDPAN BULK DATA DESCRIPTION 4 97 GRIDFRC GRIDFRC Direct Forces at FEM Grid Points Description Defines a control force at a set of structural finite element grid points Format and Example 1 2 3 4 5 6 7 8 9 10 CONT IDGRID1 COMP1 FACTOR1 REMARK1 IDGRID2 COMP2 FACTOR2 REMARK2 GRIDFRC GFORCE c Field Contents LABEL Unique alphanumeric string up to 8 characters used to identify the control surface Character See Remark 1 TYPE Type of force Character SYM Symmetric force ANTI Anti symmetric force ASYM Asymmetric force SISOID Not used GFORCE Character string referring to the name of a matrix that is imported by a DMI bulk data card or ASSIGN MATRIX Executive Control Command This matrix contains NGSET rows and one column of force at all structural d o f where NGSET 6 x numbering structural grid points Character or blank IDGRIDi Identification number of a structural finite element grid points that is imported from the ASSIGN FEM Executive Control Command Integer gt 0 See Remark 2 COMPi Component number 1 2 3 4 5 or 6 representing the degree o
96. ith roll up vortex line is placed This plane is constructed based on the three points REFGRID IDSET and GRIDU GRIDL For REFGRID 0 or blank this plane is defined by two points IDSET and GRIDU GRIDL and a tangential vector of the panels where GRIDU and GRIDL attached Integer gt 0 or Blank See Remark 9 1 The VORNET bulk data card automatically generates a set of reference grid points and connects these points by a set of internally generated CSHEAR CROD and CBAR elements to model the roll up vortex shed from the wing side edge The following figure shows a 70 degree delta wing and its sought vortex roll up model BULK DATA DESCRIPTION 4 205 VORNET 70 delta wing with vortex roll up model In this above figure there are a total of 5 vortex roll up lines 3 at the wing leading edge and 2 in the wake region entry NTIP 3 and entry NWAKE 2 The following figure is the zoom in view of the section which depicts the structure of a vortex roll up line vortex core line vortex CROD element GRIDU f vorticity feeding point GRIDL vorticity sheet Generated by following the right hand rule CSHEAR panel if TIPGRID gt 0 Section A A Each vortex roll up line consists of a set of vorticity feeding points and a vortex core located at the last vorticity feeding point In this example there are four vorticity feeding points therefore entry NFED 4 Between two vortex roll up l
97. located In the following figure the X Y Z system is the local coordinates defined by CORD2R bulk data card whereas X Y Z is the aerodynamic coordinates of the ZONAIR aerodynamic model 4 106 BULK DATA DESCRIPTION INPCFDI CFD Mesh y B C CFD Mesh 4 22267 ZAERO Aerodynamic 77 Aerodynamic IS Model Se 408 Model 27 i N y S y Points A B C of CORD2R X x Definition In the example the nose of the fuselage of the CFD surface mesh is located at x z 0 and y 100 with respect to the ZONAIR aerodynamic model whereas that of the ZONAIR aerodynamic model at x y z 0 To transform the CFD mesh it is required to specify a CORD2R bulk data card such as CORD2R 50 0 0 100 0 0 0 0 0 100 0 1 0 C 0 0 101 0 1 0 In addition because the above figure shows that the CFD surface mesh is located in the negative y axis the entry TRANSF must be a negative integer in this case TRANSF 50 to flip the CFD mesh from the negative y axis to the positive y axis The unstructured CFD mesh and solution are stored according to the following format Card Set 1 NSGRID NSELEM Free Format NSGRID Number of surface grid points Integer NSELEM Number of surface elements Integer If DATA PLOT3D Card Set 2 x z RHO RHOU RHOV RHOW E Free Format 2 and z location of the surface grid point Real
98. located see the following figure The RBE2 bulk data card must also be specified with entry CBAR NO to introduce the potential jump at GRIDU due to the wake surface generated by the thick wing component 6 DIVIDE entry defines the streamwise distribution of the NX reference grids at the ith wake line For DIVIDE SET1 these NX reference grids the input reference grids defined by the GRID 4 212 DATA DESCRIPTION WAKENET bulk data cards with entry PS Z 0 whose identification numbers are listed in the SET1 bulk data card SETID IDAEF For DIVIDE the real values listed in the AEFACT bulk data card SETID IDAEF represent the streamwise locations of these reference grids in terms of percentage of the length of the wake line the LENGTH entry Therefore these real values must be greater than 0 0 and less than or equal to 100 0 For DIVIDE COS the streamwise locations of these reference grids with respect to the GRIDU and GRIDL are computed by the following equation NX j X soos ERD i x For DIVIDE EVEN these NX reference grids are evenly distributed along the ith wake line The following figure show that the first wake line can be defined by a set of surface grid points In this case those surface grid points must be a subset of those surface grid points referred by the RBE2 bulk data card Surface Grid Points WAKENET The GRI
99. neutral file FORM NASTRAN for generating a NASTRAN bulk data deck FORM NASTL for generating a NASTRAN bulk data deck with GRID entries in large field format 1 e allows for higher degree of numerical accuracy over the FORM NASTRAN option Character Default See Remark 3 FILENM The name of the data file in which the data for plotting the deflected control surface is stored This file name is always in the upper case In case the input file name is given in the lower case the program converts it to the upper case If the first character of FILENM starts with a dollar sign the rest of the characters must be integers This integer is the identification number of an EXTFILE bulk data card where the filename is specified This feature allows for filenames up to 72 characters to be input Character AERONM The name of a data file in which the aerodynamic model is stored in a PATRAN neutral file ONLY USED IF FORM PATRAN If the first character of AERONM starts with a dollar sign the rest of the characters must be integers This integer is the identification number of an EXTFILE bulk data card where the filename is specified This feature allows for filenames up to 72 characters to be input Character Default See Remark 4 BULK DATA DESCRIPTION 4 145 PLTSURF Remarks I SETID is not referred to by other bulk data cards
100. number of an EXTFILE bulk data card where the filename is specified This feature allows for filenames up to 72 characters to be input Character AERONM The name of a data file in which the aerodynamic model is stored in PATRAN neutral file Only used if FORM PATRAN If the first character starts with a dollar sign the rest of the characters must be integers This integer is the identification number of an EXTFILE bulk data card where the filename is specified This feature allows for filenames up to 72 characters to be input Character Default AEROGEOM DAT See Remark 4 Remarks 1 IDPLT is not referred to by other bulk data card The existence of each PLTTRIM in the bulk data input triggers the generation of a data file for the post processing of the static aeroelastic trim analysis 2 Ifno TRIM bulk data card with IDTRIM existing in the Bulk Data Section the ASCII file will not be generated But this does not result a fatal error 3 IDEAS output of FORCE and MOMENT are stored in universal dataset 782 for both Left Hand Side LHS and Right Hand Side RHS load sets The ANSYS output is a FEMAP neutral file that can be read in by an ANSYS neutral file translator developed by PADT Inc also see Section 7 4 PLTTRIM 4 PATRAN requires that the aerodynamic model be stored in a neutral file and that analysis results be stored in a results file Therefore the AERONM entry is used to assign a name for a neut
101. of dn Optional function constraint functions Optional Program assigned trim variables Controlsurfacetype of trim variables User defined trim variables JEn 5 Y DMI DLINK TRIMADD TRIMFNC Optional Optional Defines a trim Defines a trim List ofa Set of TRIMINE TRIMLNK i functionasa function trim functions for Imports user supplied Defines trim function of other print out Aerodynamic pressure variable linking trim functions i coefficients i H ISSET Y Y Y IASET ISSET INPCFD INPCDF1 CPSPLN Options Optional AEFACT DMI LOADMOD DMI bulk data card List of modal Defines L gt or ASSIGN MATRIX FILENAME values component loads MNAME DMI Executive Control Command for user supplied distributed aerodynamic pressure distribution Figure 4 7 Bulk Data Interrelationship for Static Aeroelastic Trim Analysis It should be noted that for a symmetric trim system trim system involving only the longitudinal trim degrees of freedom X Z and or 4 the free vibration solution of the finite element model with symmetric boundary condition must be imported by the ASSIGN FEM Executive Control Command with BOUNDARY SYM For an anti symmetric trim system trim system involving only the lateral trim degrees of freedom the anti symmetric free vibration solution must be imported by the ASSIGN FEM Executive Control Comm
102. or NO to define the type of boundary condition on the aerodynamic surface HOTWALL YES Radioactive equilibrium boundary condition The surface temperature defined in the TEMP entry is used as the initial temperature condition HOTWALL NO Cold wall boundary condition The temperature on the surface is fixed at TEMP Character BULK DATA DESCRIPTION 4 171 THERMAL TRANS IGAS EMIS STREAM FORM FILENM AERONM Remarks Specifies the assumption of Laminar or turbulent flow TRANS 0 the program automatically determines the transition of the flow TRANS 1 entire flow is assumed to be laminar TRANS 2 entire flow is assumed to be turbulent Integer Specifies the options of real or ideal gas IGAS 0 for ideal gas IGAS 1 for ideal gas for Helium IGAS 2 for real gas Integer Emissitivity used only for HOTWALL YES Real Default 0 8 STREAM can be either a character string or integer to define the aerodynamic panels whose streamlines are included in the plot file FILENM STREAM ALL Streamline of all aerodynamic panels are included STREAM 0 No streamline is included STREAM gt 0 STREAM is an integer representing the identification number of a PANLST2 bulk data card that lists a set of panel identification numbers whose streamlines are included Character or Integer See Remark 2 FORM TECPLOT for generating a TECPLOT file FORM PATRAN fo
103. point s would occur for example if another thin wing component were defined with a wing id of say 112 since there would be two aerodynamic panels with id s of 112 and duplicate aerodynamic grids of 112 113 etc Therefore for this case the next closest wing id WID or grid id BID that could be used is 121 y X Spanwise Spanwise Strip 1 Strip NSPAN 1 101 Chordwise po Strip 1 NCHORD 4 lt Chordwise 104 29 Strip NCHORD 1 The set of identification numbers of the GRID bulk data card is to ensure a perfect match of the thin wing panels to the CTRIA3 CQUADA panels at the wing body junction so that the line vortex emanating from the wing root can be cancelled by the doublet singularity of the body panels CTRIA3 or CQUADA panels For instance the configuration illustrated below shows that the identification numbers of the GRID bulk data card are 101 107 303 and 404 Note that if LRCHD AUTO the number of surface grid points located along the wing body junction must be equal to NCHORD Otherwise a fatal error occurs For a body with non constant cross section at the wing body junction there exists a gap between the wing root and body In this situation the program will automatically create gap panels to fill in these 4 48 BULK DATA DESCRIPTION CAERO7 gaps The vortex strength of the gap panel is the same as its adjacent wing panel at the root so that no additional unknowns are introduce
104. provided 7 3 INTERPOLATED STRUCTURAL MODE SHAPE PLTMODE An output data file of the interpolated structural mode shapes on the aerodynamic model can be generated with the PLTMODE bulk data card see Figure 7 3 Viewing the interpolated structural modes is very useful in determining whether or not the aerodynamic model is properly splined to the structure Experience has shown that most errors in aeroelastic analysis are a result of incorrect spline input Therefore viewing the interpolated structural mode shapes should always be performed for verification purposes whenever the spline input 1 SPLINEI SPLINE2 SPLINE3 an ATTACH bulk data cards is modified The maximum displacement of the interpolated structural mode shape is controlled by the MAXDISP entry of the PLTMODE bulk data card MAXDISP is a fraction i e 0 0 1 0 of the reference chord length REFC entry specified in the AEROZ bulk data card Figure 7 3 Plot of an Interpolated Mode Shape on the Aerodynamic Model Mode 1 The PLTMODE output plot file contains the deformed aerodynamic model for a specified structural mode aerodynamic panel corner grid points and connectivity information of the aerodynamic model i e deformed aerodynamic model is generated The magnitude of the displacement is scaled by the SCALE entry of the PLTMODE bulk data card The data for this output file is generated by the spline SPLINE module 7 14 PLOT FILES
105. referred to by DMI bulk data cards Format and Example i 2 3 4 5 6 7 8 9 10 cm Field Contents NAME Name of the matrix NAME must be the same as the entry NAME of the DMI bulk data card Character J Column number of NAME Integer gt 0 I1 I2 etc Row number of NAME which indicates the beginning of a group of nonzero elements in the column Integer gt 0 A Ix J Real part of element see TIN of DMI bulk data card Real B Ix J Imaginary part of element see TIN of DMI bulk data card Real Remarks 1 DMIS is referred to by the DMI bulk data card with entry LARGE DMIS The size and type of the matrix is defined in the DMI bulk data card 2 The locations of the matrix elements is shown as follows 1 1 2 lt lt ACN NAME ae oo te A M 1 2 gt lt where is the number of rows and N is the number of columns M and N are defined in the DMI bulk data card 3 For symmetric matrix only the input of the upper triangular part including the diagonals is allowed i e I lt J 4 82 BULK DATA DESCRIPTION DMIS 4 Only nonzero terms need to be entered Therefore I1 I2 etc are the row locations of the first nonzero element in the J column 5 Complex input must have both the real and imaginary parts entered if either part is nonzero i e the zero components must be inputted explicitly Example of a Complex Matr
106. side force EE de Mas s M is the roll moment about REFX REFY and REFZ q b aM M is the yaw moment about REFX REFY and REFZ q Sb and 4 is the dynamic pressure S is the reference area REFS c is the reference chord REFC and b is the reference span REFB Note All aerodynamic stability derivatives are for both sides of the configuration even if only half of the configuration XZSYM YES in the AEROZ bulk data card is modeled Control Surface Type of the Trim Variables The control surface type of the trim variables are those defined in the AESURFZ AESLINK PZTMODE JETFRC and GRIDFRC bulk data cards If the character string specified in the LABEL entry of the TRIMVAR bulk data card matches the LABEL entry of AESURFZ AESLINK PZTMODE JETFRC or GRIDFRC the program computed aerodynamic stability derivatives of the control surfaces AESURFZ AESLINK PZTMODE JETFRC or GRIDFRC are used for solving the trim system The type of the aerodynamic stability derivatives depend on the TYPE entry in the AESURFZ AESLINK PZTMODE JETFRC or GRIDFRC bulk data cards For TYPE SYM they are the longitudinal aerodynamic stability derivatives For TYPE ANTT they are the lateral BULK DATA DESCRIPTION 4 199 TRIMVAR aerodynamic stability derivatives For TYPE ASYM they include both longitudinal and lateral aerodynamic stability derivatives Note The unit of the aerodynamic control surface AES
107. string used to define a label for the vortex roll up surface Character TIPGRID Identification number of a surface grid point where the roll up vortex starts Note that TIPGRID can be a negative integer This gives the generation of the roll up vortex sheet by following the left hand rule about the vortex line Otherwise it follows the right hand rule Integer Z 0 See Remark 2 NFED Number of vorticity feeding points along each vortex roll up line Integer gt 0 NTIP Number of vortex roll up lines along the wing side edge in the streamwise direction Integer gt 0 NWAKE Number of vortex roll up lines along the streamwise direction in the wake region Integer gt 0 See Remark 3 CBAR Character string either YES or NO For CBAR YES a set of CBAR elements are automatically generated and attached to the last vortex roll up line Character Default Y ES See Remark 4 4 204 DATA DESCRIPTION VORNET GRIDU GRIDL DIVIDE IDSET REFSTRT ROLLUP REFGRID Remarks For 1 i NTIP GRIDU and GRIDL are the identification numbers of two surface grid points located at the wing side edge where the ith roll up vortex line starts Note that GRIDU Z GRIDL For NTIP lt i lt NTIP NWAKE GRIDU and GRIDL are the identification numbers of two reference grid points located along the wake line that is shed from the wing tip Note that GRIDU GRIDL is allowed Integer
108. structural parameter by the superposition of modal values and the generalized modal coordinates 2 To generate NASTRAN punch file the user must specify a NASTRAN Case Control Command such as FORCE PUNCH ALL or STRESS PUNCH in the NASTRAN Case Control Section for a modal an analysis where n is the identification number of the SET NASTRAN Case Control Command to list a set of element identification numbers for output Note that the ALL option is not recommended because it produces a large amount of data which could significantly increase the ZONAIR computational time 3 Atypical NASTRAN punch file is shown as follows TITLE ACO2 MODAL ANALYSIS 1 SUBTITLE LANCZOS 2 LABEL 3 ELEMENT FORCES 4 REAL OUTPUT 5 SUBCASE ID 1 6 TYPE 34 7 EIGENVALUE 0 2910688E 03 MODE 1 8 21000 1 268963E 06 1 242571E 04 1 035389E 05 9 CONT 1 243219E 02 4 542464E 09 6 153965E 06 10 CONT 1 456141E 04 2 811976E 08 11 21020 1 036433E 05 1 251435E 02 3 007680E 05 12 CONT 2 564698E 02 9 856237E 09 6 566319E 06 13 CONT 2 457500E 04 5 680340E 08 14 27535 2 303272E 04 5 782545E 04 1 750886E 07 258 CONT 7 776543E 08 4 610047E 07 1 156353E 06 259 CONT 3 834066E 08 1 687854E 04 260 TITLE ACO2 MODAL ANALYSIS 292 SUBTITLE LANCZOS 293 LABEL 294 ELEMENT FORCES 295 REAL OUTPUT 296 SUBCASE ID 1 297 TYPE 34 298 EIGENVALUE 0 2734564E 03 MODE 2 299 21000
109. subcase section must be started by a SUBCASE n Case Control Command 2 w is an integer that assigns an identification number to the subcase section Among all SUBCASE Case Control Commands n must be unique 3 Within each subcase section only one discipline e g AEROGEN TRIM and THERMAL Case Control Commands is allowed 4 SUBTITLE and LABEL Case Control Commands must be located within each subcase section 3 40 CASE CONTROL SECTION SUBTITLE SUBTITLE Defines a Subtitle of Each Subcase Section Description Defines a subtitle of each subcase section by a character string up to 72 characters in length Format SUBTITLE Example SUBTITLE TRIM Analysis at M 0 8 Remarks 1 The SUBTITLE Case Control Command must appear within a subcase section 2 A represents a character string up to 72 characters in length that allows for additional description of the subcase section 3 Within each subcase section only one SUBTITLE Case Control Command is allowed 4 If no SUBTITLE exists in a subcase section then the character string is blank CASE CONTROL SECTION 3 41 THERMAL THERMAL Invokes the Aeroheating Analysis Discipline Description Invokes the aeroheating analysis discipline by pointing to an identification number of the THERMAL bulk data card Format THERMAL n Example THERMAL 100 Remarks 1 THERMAL Case Control Command must appear within a subcase section i e
110. that GRIDA is not used if DIVIDE SETI Integer or blank See Remark 8 An integer to define the identification number of those reference grid points internally generated by the program The identification of the first reference grid point is GRIDREF and the last point is GRIDREF NX 1 GRIDREF is not used if DIVIDE SET1 Note that GRIDREF must be properly assigned so that among all reference grid points no duplicated identification number occurs Integer gt 0 default 1 See Remark 9 The length of the ith wake line along the streamwise direction LENGTH is not used if DIVIDE SETI Real gt 0 0 default 1 0 Defines a streamwise location along the ith wake line in terms of the percentage of LENGTH At this streamwise location the angle of the ith wake line is imposed by the SLOPE entry CNTLX is not used if DIVIDE SETI 0 0 lt Real lt 100 Default 100 0 See Remark 10 1 WAKENET bulk data card automatically generates a set of reference grid points and connects these points by a set of internally generated CSHEAR elements The identification numbers of these CSHEAR elements start from IDWAKE and incrementally increase by one WAKENET is used to model a curved wake surface shed from the thick wing component 2 The following example shows a curved wake surface that is modeled by the WAKENET bulk data card There are three wake lines NY 3 and four reference grids along each wake line
111. the panels which are surrounding this grid This type of linear doublet distribution is called elementary singularity distribution as shown in Figure 5 4 unit strength S ENZ T Figure 5 4 Elementary Singularity Distribution at Grid Points GUIDELINES FOR AERODYNAMIC MODELING 5 3 At each panel two boundary conditions shown in Figure 5 5 are imposed to solve the source and doublet strength the Neumann boundary condition S J and the Dirichlet boundary condition 0 n Also the zero force condition o is imposed on the wake to satisfy the wake condition x Figure 5 5 Dirichlet and Neumann Boundary Condition on Panels and Zero Force Condition on Wake Surfaces Once the unknown doublet singularity strength at each grid point is solved the resulting doublet distribution over the entire panel model is obtained by the superposition of all elementary singularity distributions It can be seen that this resulting doublet distribution is continuous over the entire panel model if all panels are coherent with the grid points Any violation of this coherent requirement such as the one shown in Figure 5 6 can result in the discontinuity of doublet distribution Because the pressure coefficient is proportional to the derivatives of the doublet distribution the discontinuous doublet can yield an incorrect pressure jump across the incoherent panels Fun distribution S doublet distribution Coherent panels Nj panels Figu
112. the connection of the ten grid points represented by the solid circles and denoted as grid points 1 through 10 Discontinuous displacement occurs between the inboard edge of the aileron and the main wing due to the discontinuous structure between grid points 6 and 7 Because the finite element model exclusively employs plate type elements the IPS method should be selected for this case Since the IPS method is formulated based on the structural equation of an infinite plate the continuity of displacement is inherently imposed This indicates that if all of the finite element grid points shown in Figure 6 2 b are included in the spline the resultant displacement on the CAERO7 macroelement are continuous In this case failure to transfer discontinuous displacement due to the aileron will lead to incorrect aeroelastic results The correct technique to be used in this spline case is to apply the IPS method on the main wing and on the aileron separately by specifying two SPLINE1 bulk data cards The first SPLINE1 established for the main wing should include the wing boxes boxes 1 6 plus 7 8 10 and 11 and finite element grid points corresponding to the main wing only grid points 1 6 plus 8 and 9 Likewise the second SPLINE1 established for the aileron should include only those wing boxes boxes 9 and 12 and finite element grid points 5 7 9 and 10 associated with the aileron MODELING GUIDELINES OF SPLINE FOR FLEXIBLE LOADS 6 3
113. the displacements at the aerodynamic grid points The first five ID lines of data set 55 list the following information Line 1 Line 2 Line 3 Line 4 Line 5 Structural input data mode shape number Structural input data filename NONE NONE NONE A sample of the I DEAS compatible output is shown in the following figure 0 0000000000000000D 00 1 2020814895629883D 01 0 0000000000000000D 00 0 0000000000000000D 00 aL 781 1 0 0 TT 1 0000000000000000D 02 2 0 0 11 8 00000000000000000 01 3 0 0 11 8 0000000000000000D 01 4 0 0 12 1 0000000000000000D 02 zd 780 aN 94 1 100000 1 2 3 4 2 94 1 100000 5 6 7 8 3 94 100000 9 10 11 12 4 94 1 100000 13 14 15 16 55 ZONAIR MODE SHAPE OUTPUT MODE 1 FROM FILE crop f06 NONE NONE NONE 1 2 3 8 1 1 0 00000E 00 1 0 00000E 00 00000E 00 0 00000E 00 2 0 00000E 00 00000E 00 0 00000E 00 3 0 00000E 00 00000E 00 0 00000E 00 4 0 00000E 00 00000E 00 0 00000E 00 Aerodynamic J 00000E 00 00000E 00 00000E 00 00000 00 Displacements on Aerodynamic Grids 0 0000000000000000D 00 1 2020814895629883D 01 1 7000000000000000D 01 0 0000000000000000D 00 0 Grid Points 201 201 201 201 Quadrilateral Elements 00000 00 00000 00 00000 00 00000 00 0 00000 00 00000 00 00000 00 00000 00 PLOT FILES 7 17 e FEMAP Compatible Output The FEMAP compatible o
114. the first group of panels starts from all CTRIA3 and CQUAD4 panels that refer to the MATBODY bulk data card with the lowest identification number Within this group of panels CTRIA3 panels are first assigned to the J set then followed by the CQUAD4 panels The last group of panels in the J set are those refer to the MATBODY bulk data card with the highest identification number Ifa thin wing is modeled by the CAERO7 bulk data card the last set of the J set is the panels on the upper side of the CAERO7 macroelement followed by the panels on the lower side of the CAERO7 macroelement see the pressure coefficient output in the standard output file 4 114 BULK DATA DESCRIPTION JETFRC JETFRC Control Forces of Jet Description Defines a control force due to jet on a set of aerodynamic panels Format and Example 1 2 3 4 5 6 7 8 9 10 JETFRC VTHRUST Ia e Ee a o4 Es os Demi d Field Contents LABEL Unique alphanumeric string up to 8 characters used to identify the control force Character See Remark 1 TYPE Type of force Character SYM Symmetric force ANTI Anti symmetric force ASYM Asymmetric force PANLSTi Identification number of PANLSTi bulk data card defining a list of aerodynamic panels where the jet is applied JETVELi Jet velocity divided by the freestream velocity Real See Remark 2 Remarks 1 JETFRC can be selected as a control force for the ASE TRIM or transient ana
115. the output file is in ASCII with 5E16 9 format FORM FORMAT23 the output file is in ASCII with 3D23 16 format FORM UNFORM the output file is unformatted Character Default FORMAT 1 is not referred to by other bulk data cards The existence of OUTPUT4 in the bulk data input triggers the program to export the matrix Multiple OUTPUT4 input cards can co exist 2 All matrices listed in the following matrices can be exported BULK DATA DESCRIPTION 4 127 OUTPUT4 rotation d o f about x y and z On each aerodynamic box has 6 d o f namely h and h where Wik and are the displacement along x y and z directions of the aerodynamic coordinate h n and are the slope of h respectively with respect to the x axis h 7 _ oh i ax Note that UGTKG could be a highly sparse matrix of structural grid points Matrix Name Description Size rowxcolumn Type Symmetric aerodynamic influence coefficient AIC matrix relates normal wash w on each dis to Jset x Jset 50004 pressure coefficients C ie C 479000 w where Jset is the Complex Note that i is the index of a AEROGEN bulk data number of panels card 0001 Same as AJJS000 but for anti symmetric AIC matrix Jset x Jset Complex Matrices relates symmetric 6 d o f structural displacement on each panel to
116. the rest of the computers heap space can be reserved for other jobs EXECUTIVE CONTROL SECTION 3 31 SOLUTION SOLUTION Alter the Solution Sequence Description Specifies the solution sequence Format SOLUTION n Example SOL 1 Remarks 1 TheSOLUTION command is optional default is 0 2 blank space must exist between the character string SOLUTION and the negative integer 3 ndenotes an integer Currently only three options are available SOL 0 No structural FEM result is imported results are computed for the rigid aerodynamic configuration SOL 1 Structural FEM results are imported by the ASSIGN FEM Executive Control Command This allows the flexible aerodynamic loads to be computed SOL 1 Stops the program execution after the aerodynamic geometry module is computed This gives the user the option to verify the aerodynamic panel model before computing the aerodynamic solutions 3 32 EXECUTIVE CONTROL SECTION Comment Statement Description Used to insert comments into the Executive Control Section Format followed by any characters up to column 80 Example This is a test case Remarks 1 must appear in the first column 2 This command can be repeatedly used anywhere in the Executive Control Section EXECUTIVE CONTROL SECTION 3 33 3 2 Case Control Section The Case Control Section allows the following Case Control Commands
117. to include the follower force effect for flexible loads analysis is added This option is activated by specifying a negative dynamics pressure in the FLEXLD bulk data card Version 4 3 Enhancements l The aerodynamic center on each CAERO7 box is moved from 50 chord to 25 chord if the Mach number is less than one This modification gives closer agreement between ZONAIR and vortex lattice method solutions A new bulk data card called SPLINEF is added to the spline module SPLINEF allows the user to create a different spline matrix for transferring the aerodynamic forces from aerodynamic panels to structural grid points Version 4 2 calculates the area of each CAERO7 box based on that of the flat plate Version 4 3 calculates the area of each CAERO7 based on the area defined by the PAFOIL7 bulk data card modification enlarges the area of the CAERO7 boxes and changes the resulting forces of the CAERO7 Model Version 4 2 Enhancements 1 new module called FLEXLD is created in Version 4 2 to compute the aerodynamic pressures and force moment coefficients with static aeroelastic effects To invoke the FLEXLD module the user must specify a new FLEXLD case control command that refers to a new FLEXLD bulk data card A new bulk data card called CPSPLN is implemented to map the wind tunnel measured pressure coefficients onto ZONAIR aerodynamic model The CPSPLN bulk data card refers to the AEROGEN bulk data card to replace the a
118. wing component Optional VISCOUS Defines the viscous parameters for computing the skin Optional frictions VORNET Macroelement for vortex roll up model Optional WAKENET Wake macroelement for curved wake surface Optional Figure 4 2 presents a flow chart showing the interrelationship of the bulk data cards for aerodynamic geometry input 4 6 BULK DATA DESCRIPTION J PAFOIL7 PAFOIL8 4 2 2 SPLINE INPUT SPLINE MODULE AEROZ AerodynamicReference Parameters Thin Wing Arbitrary Panel Automated Panel Wake Model Aerodynamic Component Model Generation Control Force CAERO7 GRID AUTOBAR CBAR AESURFZ CQUADA AUTOROD CROD AESLINK CTRIA3 AUTOTIP CSHEAR PZTMODE RBAR AUTOVOR WAKENET JETFRC BODY7 VORNET SLICE RBE2 THKWING RELAXW PSHELL PSHEAR ACOORD MATBODY MATWAKE Figure 4 2 Bulk Data Interrelationship for Aerodynamic Geometry Input The SPLINE module is invoked only if the Executive Control Command SOLUTION 1 is specified that activates the inclusion of structural flexibility effects for flexible aerodynamic analysis In other words all bulk data cards related to the SPLINE module are used only if the Executive Control Command SOLUTION 1 is specified The bulk data cards of Spline Input define the interconnection betwe
119. x y and z axes respectively m can also be a negative integer that activates the program to perform the following tasks Replaces the imported rigid body modes by the program computed rigid body modes Forces the natural frequency and the generalized stiffness of the rigid body modes to be zero The negative m option is useful for the cases where the structural finite element analysis fails to provide well behaved rigid body modes or zero rigid body natural frequency L is optional where L is an integer representing the identification number of a grid point in the structural finite element model where the rigid body modes are referred to Note that there is a slash that separates m and L If no L is specified the program will search for a grid point in the structural finite element model that can be best referred to by the rigid body modes For NASTRAN type of finite element codes should be the R set degrees of freedom please see MSC NASTRAN User s Manual for the definition of the R set degrees of freedom and L is the grid identification number that are specified in the NASTRAN SUPORT bulk data card However if the displacement of the grid point specified in the NASTRAN SUPORT bulk data card is defined in a local coordinate system the user must transform the component numbers in the NASTRAN SUPORT bulk data card from the local coordinate system to the basic coordinate system Note that th
120. 0 0 0 0 0 0 0 0 0 0000000000000000D 00 0 00000000000000000 00 0 0000000000000000 00 0 00000000000000000 00 0 00000000000000000 00 0 0000000000000000 00 0 00000000000000000 00 0 00000000000000000 00 0 0000000000000000 00 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 Dc Quadrilateral Elements 1 450 Pressure 1 4 Output Set ZONAIR Pressure cM 0 Definition 2 0000000298023224D 01 1 7 12 PLOT FILES lt NULL gt I I 451 d der CPRE Mode 1 0 8k 0 2 Pressure 0 0 X 10 102 20 702 20 220 05 4 Output Data Vector 0 0 0 0 0 0 0 0 0 0 Definition 0 0 Or edo 427 201 1 7237762222066522D 04 202 7 4403775215614587D 05 203 7 4400115408934653D 05 204 1 7237753490917385D 04 Steps within FEMAP to View the Aerodynamic Model with Pressure ZONAIR output file generated by PLTCP bulk data card Open via File Import FEMAP Neutral the ZONAIR output neutral file of the aerodynamic model with pressure select View Redraw if the image does not appear after loading Aerodynamic grids nodes are displayed as green x s Aerodynamic panels elements are displayed as white quadrilaterals Rotate pan or autocenter the model with the Dynamic Rotate function top left button on the toolbar Node Point and Element features such as id s can be set in the View Options window Open the View Select Window From the Contour Style
121. 0 0 000 000 Eight title lines are output each beginning with a NASTRAN comment card that list the TRIM bulk data card ID number Mach number dynamic pressure and LOAD SET ID s within the current file that indicate whether the entries refer to the right hand or left hand sides of the model I DEAS Compatible FORCE MOMENT Output The output format of the ASCII text file containing I DEAS output of FORCE and MOMENT stored in universal dataset 782 for both Left Hand Side LHS and Right Hand Side RHS load sets is shown in the following figure aT 782 100 1 RIGHT HAND SIDE FLEXIBLE MODEL 90 Ae E p 5b pg 0 00000E 00 0 00000E 00 1 66503E 04 4 08355E 04 4 85924E 04 0 00000E 00 97 Be EI h SE 2 93787E 10 7 39602E 13 7 20023E 03 0 00000E 00 0 00000E 00 0 00000E 00 sl 782 101 1 LEFT HAND SIDE OF FLEXIBLE MODEL 90 4p d d 0 00000E 00 0 00000E 00 1 14435E 04 2 51545E 04 3 56345E 04 0 00000E 00 97 Ais Dic de d d 2 93787E 10 7 39602E 13 7 20023E 03 0 00000E 00 0 00000E 00 0 00000E 00 PLoT FILES 7 21 This page is intentionally left blank 7 22 PLorFiLES
122. 00 70 80 90 Se tion 20 30 40 50 60 Percent Fuselage Length Location D 10 00 1 70 80 90 Percent Fuselage Length 10 20 30 40 50 60 100 70 80 90 ZONAIR Location E 20 30 40 50 60 Percent Fuselage Length WTData 10 XOWN OCWNOu Ta qq FSS do o L Jo o e Ko 410 S o 2 Jos So ee PA EMI c L Jo 52 5 zS 8 L 550 BON 8 2 1SE o 9 se z ua 2 15 G E 8 o Ado TANT OR NOLO 11179495 do Supersonic Aerodynamics 1 2 and 2 0 Force and moment coefficients of Generic Advanced Fighter at M Whole aircraft with tip missile configuration shows the capability of ZONAIR for accurate supersonic aerodynamics on complex geometry CPU time 1s only 25 minutes on a 550 MHz PC computer 999 eA NNI V 1 6 INTRODUCTION M 1 2 2 1 a ZONAIR i 1 5 0 8 o TEST x E ZONAIR 1 0 2 i TEST 9 9 904 0 5 ja w ZONAIR i 0 o TEST 02 05 4 06 0 10 0 10 20 30 10 0 10 20 30 10 0 10 20 30 Angle of attack Angle of attack Angle of attack M 2 0 15 0 1 04 rer 0 11 0 3 4 ZONAIR al d 05 z el A 02 TEST o 0 ZONAIR o 0 53110
123. 000 02 1 570 0101 0 0 0 2 4 0 0000000000000000D 00 0 0 0000000000000000D 00 3 0000000000000000D 01 0 0000000000000000D 00 0102 0 0 0 2 4 0 0000000000000000D 00 0 3 3333000183105469D 01 3 0000000000000000D 01 0 0000000000000000D 00 0103 0 0 0 2 4 0 0000000000000000D 00 0 6 6666999816894531D 01 3 0000000000000000D 01 0 0000000000000000D 00 0104 0 0 0 2 4 0 0000000000000000D 00 0 1 0000000000000000D 02 3 0000000000000000D 01 0 0000000000000000D 00 TE Structural FEM s Grid Points 404 201 124 1 17 4 1 0 0 0 0 0 0 202 207 206 201 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0000000000000000D 00 0 0000000000000000D 00 0 0000000000000000D 00 0 0000000000000000D 00 0 0000000000000000D 00 0 0000000000000000D 00 0 0000000000000000D 00 0 0000000000000000D 00 0 0000000000000000D 00 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 9 Quadrilateral Elements 7 6 PLOT FILES Steps within FEMAP to View the Aerodynamic Model ZONAIR output file generated by the PLTAERO bulk data card Open via File Import FEMAP Neutral the ZONAIR output neutral file of the aerodynamic model select View Redraw if the image does not appear after loading Aerodynamic grids nodes are displayed as green x s Structural FEM grids points are displayed as red s Aerodynamic panels elements are displayed as white quadrilaterals
124. 0000000D 00 3 0000000000000000D 01 0 0000000000000000D 00 102 0 0 IT 2 0000000000000000D 01 3 0000000000000000D 01 0 0000000000000000D 00 103 0 0 EE 4 0000000000000000D 01 1 780 201 94 202 207 202 94 203 208 203 94 204 209 204 94 3 0000000000000000D 01 im Structural FEM Grid Points 1 100000 1 1 1 4 206 201 1 100000 2 1 EH 4 207 202 1 100000 1 1 1 4 208 203 1 100000 1 4 Quadrilateral 0 0000000000000000D 00 Elements PLOT FILES 7 5 e FEMAP Compatible Output The FEMAP compatible output is saved in the FEMAP Version 7 0 neutral file format Data Blocks 403 and 404 are used to output the aerodynamic grids and panels respectively Data Block 570 is used to output the structural grid points if requested in the PLTAERO bulk data card A sample of the FEMAP compatible output is shown in the following figure 1 100 Neutral File Header followed lt NULL gt 4 amp 4 by other required Data 7 Blocks 1 5 403 201 0 0 46 0 0 0 0 0 0 1 0000000000000000D 02 0 0000000000000000D 00 0 0000000000000000D 00 0 202 0 0 46 0 0 0 0 0 0 1 0000000000000000D 02 0 0000000000000000D 00 0 0000000000000000D 00 0 203 0 0 46 0 0 0 0 0 0 1 0000000000000000D 02 0 0000000000000000D 00 0 0000000000000000D 00 0 204 0 0 46 0 0 0 0 0 0 0000000000000000D 00 ON Aerodynamic Grid Points 0 1 0000000000000
125. 00000E 00 10102 0 00000E 00 0 00000E 00 0 26822E 02 0 16414 03 0 65124E 03 0 00000E 00 10103 0 00000E 00 0 00000E 00 0 25368E 00 0 12338 01 0 13857E 01 0 00000E 00 10104 0 00000E 00 0 00000E 00 0 74296E 00 0 11283 01 0 15286E 01 0 00000E 00 10201 0 00000E 00 0 00000E 00 0 42818 01 0 25493 02 0 46822E 02 0 00000E 00 10202 0 00000E 00 0 00000E 00 0 20886E 00 0 10183E 01 0 13360E 01 0 00000E 00 10203 0 00000E 00 0 00000E 00 0 60133E 00 0 10444 01 0 14346E 01 0 00000E 00 10204 0 00000E 00 0 00000E 00 0 10163E 01 0 11942 01 0 15326E 01 0 00000E 00 10301 0 00000E 00 0 00000E 00 0 27369E 00 0 97731 02 0 15390E 01 0 00000E 00 10302 0 00000E 00 0 00000E 00 0 60821E 00 0 10325 01 0 14585E 01 0 00000E 00 10303 0 00000E 00 0 00000E 00 0 94650E 00 0 11739 01 0 15463E 01 0 00000E 00 10304 0 00000E 00 0 00000E 00 0 12921E 01 0 11467 01 0 15467E 01 0 00000E 00 10401 0 00000E 00 0 00000E 00 0 77468E 00 0 10832 01 0 15439E 01 0 00000E 00 10402 0 00000E 00 0 00000E 00 0 10378E 01 0 11649 01 0 16002E 01 0 00000E 00 10403 0 00000E 00 0 00000E 00 0 13044E 01 0 11356 01 0 15649E 01 0 00000E 00 10404 0 00000E 00 0 00000E 00 0 15664E 01 0 11907 01 0 15638E 01 0 00000E 00 20000 0 00000E 00 0 00000E 00 0 00000E 00 0 00000E 00 0 00000E 00 0 00000E 00 MODE 2 0 73496E 02 0 10000E 01 10101 0 00000E 00 0 00000E 00 0 22488E 00 0 27753E 01 0 11296 01 0 00000E 00 10102 0 00000E 00 0 00000E 00 0 56264E 02 0 36655E 03 0 1306
126. 000E 00 0 0000E 00 0 0000E 00 5 1654 03 3 2127E 01 1 0999 04 5 6140E 02 1 9791 04 1 6990E 03 0004 5 1500 00 1 5780E 06 3 0000 00 0 0000 00 0 0000E 00 0 0000 00 0 0000E 00 6 3605 03 1 2547 01 1 1067E 04 1 2254E 04 1 9173 04 6 6229E 04 0005 8 8000E 00 1 5780E 06 3 0000 00 0 0000 00 0 0000E 00 0 0000 00 0 0000E 00 5 2456E 03 1 6441 00 1 1292 04 3 1720E 03 1 9339E 04 2 7381E 04 0006 1 5000E 00 3 1560E 06 3 0000 00 0 0000 00 0 0000E 00 0 0000 00 0 0000 00 1 3660 04 7 3367E 00 1 0569 04 4 2465E 03 1 9974 04 1 0582E 04 0007 5 1500 00 3 1560E 06 3 0000E 00 0 0000E 00 0 0000 00 0 0000E 00 0 0000 00 5 1512 04 2 2051E 02 6 5877E 03 2 1063 05 1 6333E 04 1 1364E 06 0008 8 8000E 00 3 1560E 06 3 0000 00 0 0000 00 0 0000E 00 0 0000E 00 0 0000E 00 3 0403E 04 2 7328 01 9 7425 03 5 1925 04 1 9257 04 4 4761E 05 0009 1 5000E 00 0 0000 00 1 6500 01 0 0000 00 0 0000E 00 0 0000 00 0 0000E 00 1 5877 04 2 5960 01 4 3676 04 1 8265E 02 7 2515 04 3 2579E 02 0010 5 1500E 00 0 0000E 00 1 6500 01 0 0000 00 0 0000 00 0 0000E 00 0 0000E 00 1 5466E 04 1 2262E 00 4 3661E 04 1 9281E 03 7 1762E 04 6 7346E 03 0011 8 8000E 00 0 0000E 00 1 6500 01 0 0000 00 0 0000 00 0 0000E 00 0 0000E 00 1 5245E 04 8 9774 01 4 3311E 04 7 3544 02 7 1111 04 2 0132E 03 0012 1 5000 00 1 5780E 06 1 6500
127. 00E 00 10201 0 00000E 00 0 00000E 00 0 75121E 00 0 41058 01 0 30717 02 0 00000E 00 10202 0 00000E 00 0 00000E 00 0 68298E 00 0 37961 01 0 33754 02 0 00000E 00 10203 0 00000E 00 0 00000E 00 0 53470E 00 0 38371 01 0 62558 02 0 00000E 00 10204 0 00000E 00 0 00000E 00 0 51272E 00 0 98467 01 0 71547E 02 0 00000E 00 10301 0 00000E 00 0 00000E 00 0 74286E 00 0 21605E 01 0 24621 01 0 00000E 00 10302 0 00000E 00 0 00000E 00 0 33082E 00 0 60365E 01 0 11344 01 0 00000E 00 10303 0 00000E 00 0 00000E 00 0 48071E 00 0 48408E 01 0 25199E 01 0 00000E 00 10304 0 00000E 00 0 00000E 00 0 14509E 01 0 21497E 01 0 62914E 01 0 00000E 00 10401 0 00000E 00 0 00000E 00 0 16873E 01 0 11807E 00 0 39602 01 0 00000E 00 10402 0 00000E 00 0 00000E 00 0 19794E 01 0 11497E 00 0 81029E 02 0 00000E 00 10403 0 00000E 00 0 00000E 00 0 14617E 01 0 11634E 00 0 53803E 01 0 00000E 00 10404 0 00000E 00 0 00000E 00 0 33004E 00 0 11116E 00 0 81777E 01 0 00000E 00 20000 0 00000E 00 0 00000E 00 0 00000E 00 0 00000E 00 0 00000E 00 0 00000E 00 Remark 9 of ASSIGN FEM Since the geometry of an aircraft is usually symmetric about a vertical plane passing through the center line of the fuselage only half of the aircraft is required to be modeled structurally as well as aerodynamically The symmetric modes and anti symmetric modes of the aircraft structure can be obtained by imposing the so called symmetric boundary condition and anti symmetric bounda
128. 0102 0 1 0 0 0 0 0 0 300000000 02 0 333330002E 02 0 000000000E 00 31 10103 0 1 0 0 0 0 0 0 300000000E 02 0 666669998E 02 0 000000000E 00 Ton Structural FEM Grid Points 99 0 0 1 0 0 0 0 0 Data Packets 1 Node Data and 2 Element Data are used to output the aerodynamic grid points and aerodynamic panels respectively Data Packet 31 Grid Data is used to output the structural grid points if requested the PLTAERO bulk data card i e FEMGRID Z YES PLOT FILES 7 3 Steps within PATRAN to View the Aerodynamic Model ZONAIR output file generated by the PLTAERO bulk data card Open anew PATRAN database Read in the geometry file Select File Import from the Radio buttons Object Model Source Neutral select the appropriate geometry neutral file and click Apply e Tecplot Compatible Output A sample of the Tecplot compatible output is shown as follows 65 TITLE AERO MODEL WITH VARIABLE X Y Z ZONE I 91 AERO GRIDS amp 17 FEM GRIDS AERO PANELS EXTID 1 0000E 02 1 0000E 02 1 0000E 02 1 0000E 02 Nu BWD 108 J 65 F FEPOINT 0 0000E 00 0 0000E 00 201 Grid Point 0 0000E 00 0 0000E 00 202 Identification Numbers 0 0000E 00 0 0000E 00 203 0 0000E 00 0 0000E 00 204 Aerodynamic Grid Points X Y Z 7 6 1 Aerodynamic Connectivity 8 7 2 Information aero panels i 2 e g the first line connects the 2nd 7th 6th and 12 11 6 Ist aero grid points listed above TITL
129. 02 1 173877 02 1 146654 02 1 083210 02 1 164881 02 1 135552 02 1 190655E 02 0 0 OR NO R1 2 775307E 02 3 665544E 04 2 015278E 02 3 048569E 02 1 869456E 02 2 759980E 02 2 518181E 02 3 147953E 02 3 588441E 02 3 148519E 02 3 430069E 02 3 505625E 02 3 543852 02 3 705165E 02 3 638719E 02 3 727286E 02 0 0 OR NO R1 4 772991E 02 2 285311E 03 3 340588 04 4 635419 02 2 147846 02 3 574188 02 2 010099 02 4 816738 02 2 839814 02 9 244961 03 2 670205E 02 5 703675E 02 1 441457E 02 2 155319E 02 4 181003E 02 4 735287E 02 0 0 OR NO R1 2 694899E 04 1 243020E 03 6 215813E 03 3 207996E 02 3 459100E 02 GENERALIZED zx nd 4 3 7 1 2 23 zu 2 2 2 2 2 2 2 WRN A CUNAHRAWWWRPPAIW 2 S5 2 6 OpHBpppBppBppppPhpHon MASS 000000 00 000000 00 000000 00 000000 00 000000 00 R2 388628E 02 512418E 04 385677E 02 528565E 02 682182Eb 03 336013E 02 434578E 02 532579E 02 539033E 02 458461E 02 546269E 02 546714E 02 543930E 02 600222E 02 564861E 02 563803E 02 0 R2 129584E 02 306792 03 288727 02 250301E 02 974025E 03 968281E 02 596193E 02 677993E 02 368388E 02 168402 02 810665E 02 956726E 02 199665E 02 421410E 02 723050E 02 898597E 02 0 0 R2 532157E 02 063501E 03 785009E 02 239622 02 023199E 02 08403
130. 02 etc The X axis specified by the ACOORD bulk data card defines the centerline of the body macroelement If ACOORD entry is zero the X axis of the basic coordinate system is used The number of aerodynamic grids and panels generated by each segment is 1 NAXIS 1 x NRAD and NAXIS 1 NRAD 1 respectively therefore there are 1 NAXIS x NRAD and NAXIS 1 NRAD 1 number of grids and panels respectively for each BODY7 bulk data card For instance if BID 101 NAXIS 5 and NRAD 4 the grid and panel identification number are shown below ACCORD Grid Identification Numbers Panel Identification Numbers For a blunt nose body in hypersonic flow the local Mach number at the nose often becomes subsonic which needs special treatment The following figure shows a body that consists of a round nose a cone and a cylinder For this type of body IAXIS should be the axial station where the cone ends In other words IAXIS covers both the round nose and the cone For the following figure IAXIS 8 4 42 BULK DATA DESCRIPTION BODY7 IAXIS 8 NOSERAD S cone cylinder round nose NRAD 1 number of CBAR elements are generated which are connected by those grid points located at the last axial stations NAXIS The identification numbers of those CBAR elements begin with BID NAXIS 1 X NRAD 1 See figure below for example 11 CBAR There are three methods to define the circumferential points at
131. 06E 03 0 27850 01 0 00000E 00 10104 0 00000E 00 0 00000E 00 0 13585E 01 0 46354E 01 0 12396 01 0 00000E 00 10201 0 00000E 00 0 00000E 00 0 11177E 01 0 21478E 01 0 30232E 01 0 00000E 00 10202 0 00000E 00 0 00000E 00 0 59202E 00 0 35742E 01 0 30840E 02 0 00000E 00 10203 0 00000E 00 0 00000E 00 0 53507E 00 0 20101 01 0 70681E 02 0 00000E 00 10204 0 00000E 00 0 00000E 00 0 28988E 00 0 48167 01 0 11452E 01 0 00000E 00 10301 0 00000E 00 0 00000E 00 0 13261E 01 0 28398E 01 0 16571E 01 0 00000E 00 10302 0 00000E 00 0 00000E 00 0 68290E 00 0 92450 02 0 38396E 01 0 00000E 00 10303 0 00000E 00 0 00000E 00 0 14758E 00 0 26702 01 0 38794E 01 0 00000E 00 10304 0 00000E 00 0 00000E 00 0 96577E 00 0 57037 01 0 35297E 01 0 00000E 00 10401 0 00000E 00 0 00000E 00 0 79032E 00 0 14415 01 0 62191E 01 0 00000E 00 10402 0 00000E 00 0 00000E 00 0 25718E 00 0 21553 01 0 60484E 01 0 00000E 00 EXECUTIVE CONTROL SECTION 3 17 ASSIGN FEM 10403 0 00000E 00 0 00000E 00 0 12534E 01 0 41810 01 0 59708E 01 0 00000E 00 10404 0 00000E 00 0 00000E 00 0 22190E 01 0 47353 01 0 56136E 01 0 00000E 00 20000 0 00000E 00 0 00000E 00 0 00000E 00 0 00000E 00 0 00000E 00 0 00000E 00 MODE 4 0 27096E 03 0 10000E 01 10101 0 00000E 00 0 00000E 00 0 41233E 01 0 26949E 03 0 22664E 00 0 00000E 00 10102 0 00000E 00 0 00000E 00 0 23187E 01 0 12430 02 0 53145 02 0 00000E 00 10103 0 00000E 00 0 00000E 00 0 45206E 00 0 62158 02 0 21217 0
132. 0E 00 2 79537 01 1 80782E 02 2 91873E 04 0 00000E 00 10203 G 0 00000E 00 0 00000E 00 2 61509 01 7 86821E 03 3 22475E 03 0 00000E 00 10204 G 0 00000E 00 0 00000E 00 1 33835E 01 2 23012 02 6 19697E 03 0 00000E 00 10301 G 0 00000E 00 0 00000E 00 6 44802 01 1 60531 02 5 98641E 03 0 00000E 00 10302 G 0 00000E 00 0 00000E 00 3 71222 01 2 48809E 03 1 76481E 02 0 00000E 00 10303 G 0 00000E 00 0 00000E 00 2 27884E 02 1 12650E 02 1 89721E 02 0 00000E 00 10304 G 0 00000E 00 0 00000E 00 4 31970E 01 2 59648E 02 1 80001E 02 0 00000E 00 10401 G 0 00000E 00 0 00000E 00 4 65978 01 4 68261E 03 2 96838E 02 0 00000E 00 10402 G 0 00000E 00 0 00000E 00 3 61408E 02 9 01868E 03 2 95462E 02 0 00000E 00 10403 G 0 00000E 00 0 00000E 00 5 21803E 01 1 88400E 02 2 95140E 02 0 00000E 00 10404 G 0 00000E 00 0 00000E 00 1 00000E 00 2 15487E 02 2 79225E 02 0 00000E 00 20000 G 0 00000E 00 0 00000E 00 0 00000E 00 0 00000E 00 0 00000E 00 0 00000E 00 ASTROS VERSION 21 2 B04 10 09 P LI FINAL ANALYSIS SEGMENT DEMO CASE MODES ANALYSIS BOUNDARY 1 MODE 4 REAL EIGENVECTOR FOR MODE 4 EIGENVALUE 4 18786E 04 RAD S 2 EXECUTIVE CONTROL SECTION 3 11 ASSIGN FEM CYCLIC FREQUENCY 3 25699E 01 HZ POINT ID TYPE TI T2 T3 R1 R2 R3 10101 G 0 00000E 00 0 00000E 00 1 00000E 00 2 01715E 03 5 64829E 02 0 00000E 00 10102 G 0 00000E 00 0 00000E 00 4 92003E 03 2 67899E 04 1 21958E 03 0 00000E 00 10103 G 0 00000E 00 0 00000E 00 7 22189 02 8 02059
133. 1 0 00000E 00 10104 0 00000E 00 0 00000E 00 0 24405E 00 0 32080E 01 0 30962E 01 0 00000E 00 10201 0 00000E 00 0 00000E 00 0 12838E 01 0 34591E 01 0 61634 01 0 00000E 00 10202 0 00000E 00 0 00000E 00 0 15769E 00 0 96841E 03 0 31703 01 0 00000E 00 10203 0 00000E 00 0 00000E 00 0 28700E 00 0 64437 02 0 22880E 01 0 00000E 00 10204 0 00000E 00 0 00000E 00 0 43259E 00 0 24939 01 0 26221E 01 0 00000E 00 10301 0 00000E 00 0 00000E 00 0 26374E 00 0 30151E 01 0 23570 01 0 00000E 00 10302 0 00000E 00 0 00000E 00 0 49179E 00 0 14120E 01 0 97932 02 0 00000E 00 10303 0 00000E 00 0 00000E 00 0 95931E 02 0 48406 02 0 33432E 01 0 00000E 00 10304 0 00000E 00 0 00000E 00 0 91641E 00 0 17010 01 0 47363E 01 0 00000E 00 10401 0 00000E 00 0 00000E 00 0 98708E 00 0 26191E 01 0 21474E 01 0 00000E 00 10402 0 00000E 00 0 00000E 00 0 51999E 00 0 99015E 02 0 39578E 01 0 00000E 00 10403 0 00000E 00 0 00000E 00 0 26106E 00 0 83701E 03 0 53131E 01 0 00000E 00 10404 0 00000E 00 0 00000E 00 0 11794E 01 0 71778 02 0 54558E 01 0 00000E 00 20000 0 00000E 00 0 00000E 00 0 00000E 00 0 00000E 00 0 00000E 00 0 00000E 00 MODE 5 0 44812E 03 0 10000E 01 10101 0 00000E 00 0 00000E 00 0 19766E 01 0 94727 01 0 11470E 00 0 00000E 00 10102 0 00000E 00 0 00000E 00 0 22769 01 0 13900 02 0 94413E 03 0 00000E 00 10103 0 00000E 00 0 00000E 00 0 87766E 00 0 79747E 01 0 52134 01 0 00000E 00 10104 0 00000E 00 0 00000E 00 0 24558E 01 0 13721E 00 0 38673E 01 0 000
134. 1 2 1 2 Pood Poo ds 2 2 BULKDATA DESCRIPTION 4 109 INPCFDI since 02 242 a2 and Poo CP aon 2 1 Cp ni 5 Local Mach Number Mi Mach number is defined as _ Yeo It follows that local Mach number is therefore defined as y a where the absence of ee indicates local values Since the total velocity is the magnitude of the velocity components y yu 2 u id tye w y 0 Us Minp and since locally 42 substituting A 2 through A 5 we get 2 2 2 2 2 2 2 2 2 a d y TR Uso Us 2 2 2 Wa ta twa Minp Mo Tfy B 4 B 5 4 110 BULK DATA DESCRIPTION INPCFDI 6 Density Pinp Defining the non dimensional density as p Poo Per the ideal gas law density is defined 7 TR It follows that the local density is defined as p where the absence of ee indicates TR local values Since 42 yRT and V solving for R we get doo R Us YM Ton substituting this into the local density defined above and rearranging we have T 2 non dimensionalizing the equation by dividing both sides by and rearranging yields p 2 p 05 2 Pinn M5 inp Poo T Too substituting A 1 and A 5 yields
135. 1 811090503E 02 4 0 57 96611 1 515793658E 01 96617 3 24 EXECUTIVE CONTROL SECTION ASSIGN MATRIX 854211102E 96619 419543836E 96709 1 052054613E 5 96611 4 641623764E 96617 8 665747224E 96619 271699994E 96709 9 484510803E 6 02 03 02 0 02 03 03 03 1 1 026752114 00 For Non Sparse and Binary Format 57 FORM UNFORMAT Record 1 Word Type NCOL NROW NF WORD1 WORD2 418 8 Numbers 1 Integer NCOL Number of columns 2 Integer NROW Number of rows 3 Integer NF Form of matrix NF 2 General rectangular matrix NF 6 Symmetric matrix Only the upper triangular including diagonals is inputted 4 Integer NTYPE Type of matrix NTYPE 1 Real single precision NTYPE 2 Real double precision NTYPE 3 Complex single precision NTYPE 4 Complex double precision Character string up to 8 characters 5 and 6 Character WORDI Two character string Each has 4 characters WORD2 If no MNAME c is specified these characters are used as the name of the matrix EXECUTIVE CONTROL SECTION 3 25 ASSIGN MATRIX Record 2 Word Type ICOL IROW NW A J J IROW IROW NW NC ND 1 Number 1 Integer ICOL Column number 2 Integer IROW Row position of first nonzero term 3 Integer NW Number of words in the column NW Real A For Rs us NTYPE 1 NC 1 ND 1 and Ais areal single precision array gt
136. 11 56 ZONAIR PRESSURE MODE 1 MACH NO 1 2000 K 0 2000 CP REAL PRESSURE FOR PLTCP BULK DATA CARD WITH ID 25 NUMBER OF AERODYNAMIC GRID POINTS IN MODEL 91 NUMBER OF AERODYNAMIC BOXES IN MODEL 65 REAL COMPONENT OF PRESSURE CP RE 1 1 1 18 2 1 1 1 1 0 00000E 00 201 1 0 00000E 00 202 1 0 00000E 00 203 0 00000E 00 Pressures e FEMAP Compatible Output The FEMAP compatible output is saved in the FEMAP Version 7 0 neutral file format Data Blocks 403 and 404 are used to output the aerodynamic grids and panels respectively Data Block 450 is used to output the pressure and local Mach number output set definition Data Block 451 is used to output two data vectors to display the results sample of the FEMAP compatible output is shown in the following figure 1 100 Neutral File Header followed FUE by other required Data 7 2 Blocks 1 403 201 0 0 q 46 0 0 0 0 0 0 1 0000000000000000D 02 0000000000000000D 00 0 0000000000000000 00 0 202 0 0 1 46 0 0 0 0 0 0 1 0000000000000000D 02 0000000000000000D 00 0 0000000000000000 00 0 203 0 0 1 46 0 0 0 0 0 0 1 0000000000000000D 02 0000000000000000D 00 0 0000000000000000 00 0 204 0 0 qs 46 0 0 0 0 0 0 1 0000000000000000D 02 0000000000000000D 00 Aerodynamic Grid Points 1 404 201 124 i 17 4 17 0 0 0 0 0 0 202 207 206 201 0 0 0 0 0 0 0 0
137. 2 10204 G 0 0 0 0 5 127236E 01 9 846668 02 10301 G 0 0 0 0 7 428587E 01 2 160513E 02 10302 G 0 0 0 0 3 308228E 01 6 036545E 02 10303 G 0 0 0 0 4 807106E 01 4 840772 02 10304 G 0 0 0 0 1 450914E 00 2 149668E 02 10401 G 0 0 0 0 1 687299E 00 1 180740E 01 10402 G 0 0 0 0 1 979366 00 1 149720 01 10403 G 0 0 0 0 1 461685E 00 1 163374E 01 10404 G 0 0 0 0 3 300396E 01 1 111649E 01 20000 G 0 0 0 0 0 0 0 0 3 170266E 02 0 0 2 288025E 02 0 0 2 622103E 02 0 0 2 357039E 02 0 0 9 793158E 03 0 0 3 343225E 02 0 0 4 736346E 02 0 0 2 147435E 02 0 0 3 957807E 02 0 0 5 313112 02 0 0 5 455842E 02 0 0 0 0 0 0 5 R2 R3 1 147041E 01 9 441336E 04 5 213426E 02 3 867267E 02 3 071724E 03 3 375415E 03 6 255790E 03 7 154678E 03 2 462126E 02 1 134401E 02 2 519936E 02 6 291359E 02 960162E 02 102916E 03 380255E 02 177724E 02 0 Ooooooooooooooooo Ooooooooooooooooo Remark 5 of ASSIGN FEM If FORM ASTROS the following three commands must exist in the solution control section of the input as well as output file that generates the ASTROS solution output file a MODES PRINT MODES ALL DISP ALL ROOT BEGIN BULK SORT Please see the ASTROS User s Manual for a description of the above commands A sample output file of ASTROS free vibration analysis is shown below ASTROS RESOURCE COMMANDS ECHO Xitx L0s225 5 2205 2 2 230 oe 525 40 vL
138. 2 032439E 07 2 753735E 05 1 646139E 06 300 CONT 2 614506E 01 7 214478E 10 1 307391E 04 301 CONT 1 409557E 05 3 745799E 08 302 21020 1 775028E 06 2 614317E 01 4 958345E 06 303 CONT 7 044209E 01 1 591658E 09 2 214946E 04 304 CONT 2 378039E 05 1 662002 07 305 27535 6 439090 04 7 998943E 05 2 486631E 07 549 CONT 1 699664E 08 1 287321E 06 1 600129E 07 550 CONT 2 293527E 07 4 723957E 04 551 In the example shown above each element has 8 components of modal values The entry FIELD is used to select a particular component for output 4 138 BULK DATA DESCRIPTION PLTAERO PLTAERO ASCII Text File Generation for Plotting Description the Aerodynamic Model Defines name of a data file on which the data for plotting the aerodynamic model is stored Format and Example Field SETID THKWING FEMGRID OFFSET FORM FILENM WAKE 1 2 3 4 5 6 7 8 9 PLTAERO SETID THKWING FEMGRID OFFSET FORM FILENM 10 Contents Identification number Integer gt 0 See Remark 1 Character string either YES or NO For THKWING YES the thickness of the aerodynamic panels generated by the CAERO7 bulk data card is included both upper and lower surfaces are presented in the ASCII text file Otherwise only the mean plane of the CAERO7 bulk data is included Character Default NO Character string either YES or NO Flag for the choice of inclusi
139. 2 7 2 SERVER INSTALLATION AND OPERATIONS For details regarding the ZLS installation and operation please refer to Section 3 of ZLS User s Manual 2 7 3 ENVIRONMENT VARIABLES To run ZONAIR the following environment variables are required 1 PATH variable needs to include ZONAIR home directory which is specified at installation ZONAIREXE is set to the ZONAIR home directory location It should end with for Windows and end with for UNIX and Linux 3 ZLS ZONAIR is set to the IP of the machine hosting ZLS If ZONAIR is run on the same machine that hosts the ZLS i e a node locked setup the value of ZLS_ZONAIR should be set to Localhost 4 ZLS SERVER is set to the ZLS home directory for node locked installations 2 10 How TO RUN ZONAIR 2 7 4 THE ZONA LICENSE MONITOR The ZONA License Monitor is a Windows program that provides a convenient interface for ZLS operations including the ability to Start or Stop the ZLS to load a new license file and to view the status of the current token usage i e what s checked out The ZONA License Monitor is only available on the machine hosting the ZLS In the case of a node locked installation of ZONAIR both the ZLS and the ZONA License Monitor will exist on the same machine For details on usage of the ZONA License Monitor please refer to Section 6 of ZLS User s Manual 2 7 5 LOCKED TOKENS AND THE CLEANUP UTILITY ZONAIR is designed to operate in the following way When
140. 3 1914983001579172D 03 UI Ui amp gd 681525813481753D 02 5617263119365574D 02 2398198156757896D 02 179512947055147D 01 7468784150169609D 02 4019675274132945D 02 7297341338640479D 03 730473266346012D 02 0 3743652572097349D 02 0 182337803036962D 03 6501226652201383D 02 3136186294985838D 01 EXECUTIVE CONTROL SECTION 3 15 ASSIGN FEM Remark 8 of ASSIGN If FORM FREE it is assumed that the free vibration solution of the finite element model is obtained by some other structural finite element code In this case it is the user s responsibility to set up the modal data in file according to the following data format There are four input card sets required to construct the file a Each card set may contain one or a group of input cards Card Set 1 NGRID NMODE Free Format NGRID Number of structural grid points of the finite element model Integer gt 0 NMODE Number of structural modes Integer gt 0 Example 17 5 Card Set 2 ID x y z Free Format ID Identification number of the structural grid points Integer gt 0 2 and z locations of the grid points Real Example 100 1 0 30 0 0 Repeat card set 2 NGRID times for all structural grid points Card Set 3 FREQ GENM Free Format FREQ Natural frequency of the mode rad sec Re
141. 3 0000 01 0 0000 00 0 0000E 00 0 0000E 00 0 0000E 00 4 2186E 04 3 8035 00 6 7928E 04 3 0840E 04 1 2229E 05 3 8979E 04 0022 5 1500 00 1 5780E 06 3 0000E 01 0 0000 00 0 0000 00 0 0000E 00 0 0000E 00 4 1593E 04 5 0351E 01 6 2696E 04 4 3075 04 1 1435 05 8 8017E 04 0023 8 8000E 00 1 5780E 06 3 0000 01 0 0000 00 0 0000E 00 0 0000 00 0 0000 00 3 9371 04 1 1889E 01 6 1769 04 3 1468 04 1 1144 05 5 5046E 04 0024 1 5000 00 3 1560E 06 3 0000E 01 0 0000 00 0 0000 00 0 0000E 00 0 0000 00 5 1238 04 2 6218 01 6 2284E 04 1 2330E 05 1 2191E 05 1 5767E 05 0025 5 1500 00 3 1560E 06 3 0000E 01 0 0000 00 0 0000 00 0 0000E 00 0 0000 00 9 5214E 04 8 6174E 02 3 4684E 04 7 4185E 05 1 1933E 05 1 5154E 06 0026 8 card 6 8000 00 3 1560 06 3 0000 01 0 0000 00 0 0000E 00 0 0000E 00 0 0000E 00 7 2894 04 1 9852E 02 4 8503 04 5 1925E 05 1 2061 05 9 0796E 05 0027 BULK DATA DESCRIPTION 4 93 GENBASE Card 1 Card 2 Card 3 Card 4 Card 5 Character string that is specified by the TITLE Case Control Command Character string specified by the GEOFILE entry on which the aerodynamic panel data is stored Character string where REFC REFB REFS REFX REFY REFZ No AESURFZ LENGTH MASS UNIT Reference chord Reference span Reference area X location of the momentum center Y location of the moment
142. 450 Interpolated Mode 1 4 Output Set Mode a 4 613 Hz aoe 0 2 Definition 4 6127114295959473D 00 1 lt NULL gt Interpolated Mode 451 Output Set x i ij Definition ZONAIR Total Translation Qu Ou 027 2 3 4 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 054052 X 275 Interpolated Mode 1 1 1 Output Data Vector 1 0 0000000000000000 00 zu 2 0 0000000000000000 00 3 0 0000000000000000D 00 4 0 0000000000000000D 00 7 18 PLOT FILES Steps within FEMAP to View the Deformed or Animated Interpolated Mode Shape ZONAIR output file generated by PLTMODE bulk data card Open via File Import FEMAP Neutral the ZONAIR output neutral file of the aerodynamic model with interpolated mode deformation select View Redraw if the image does not appear after loading Aerodynamic grids nodes are displayed as green x s Aerodynamic panels elements are displayed as white quadrilaterals Rotate pan or autocenter the model with the Dynamic Rotate function top left button on the toolbar Node Point and Element features such as id s can be set in the View Options window Open the View Select Window animate the flutter mode from the Deformed Style section click on the Animate button To statically view the flutter mode from the Deformed Style section click on the Deform button Click on the Deformed and Contour Data button bar n the window that opens u
143. 47550420D 05 8310472989868395D 05 1358544160900551 05 5617118452227373D 04 OY Ui amp Ul Ul 1517800567316923 01 1067939139898222D 16 UNIT M 2 0000 00 0 9113519999999997D 01 M END TITLE 6270452321170384D 04 7268882809304363D 03 4243476398549203D 03 3264161266023014D 02 6565833985373308D 02 4677584975980958D 02 5269019719698231D 03 7193417522388700D 03 1565697075052970D 03 9436596571633759D 03 oo Oo G4 END MONVAL MONVAL 2 TITLE KIND DISP NAME SELECT WING NODE 2 TYPE TY COORD 0 2940557999999999D 00 0 0000000000000 oot 3770965314259045D 03 8641032168708783D 03 1115622083120243D 01 1459664532940326D 01 1217856158745318D 01 2097598934419818D 01 29557752934722490 02 5516094061587379D 03 9836643468589825D 04 1392135637645999D 03 UNIT M 0000 00 0 9113519999999997D 01 M END TITLE 6631092559614345D 04 0 2216313171525446D 02 0 2057090096506267D 02 4468904163869089D 02 Oo 4294748421913158D 1109663982879969D 1378020961229076D 2515687853345272D 1470923534883928 1576836534608606 3794707603699266 2534322578184867 3016114918583113 8090181085815273 1020468025402302 6759217887003857D 14 2327751708509681D 04 3429857074005640D 04 3624751739196352D 04 1598938947169428D 05 3689883842386831D 04 3608598589997129D 05 4296049769816649D 0
144. 5 INPCFD1 NORMCFD XSCALE GAMMA XFORM FILEMESH FILESOL AERONM Remarks NORMCTD 1 solution is normalized for 1 0 1 0 NORMCTD 2 solution is normalized for 1 0 1 0 NORMCTD 3 solution is normalized for 1 0 V 1 0 where 5 is the freestream speed density 15 the freestream spread of sound P is the freestream pressure and V is the freestream velocity Integer gt 0 Default 1 A global scale factor applying to the x y and z of all CFD grid points Real gt 0 0 Default 1 0 Specific heat ratio used in the CFD computation Real gt 1 0 default 1 4 Format of the output file specified in the entities FILEMESH and FILESOL FORM TECPLOT for generating a TECPLOT file FORM PATRAN for generating a PATRAN neutral file FORM IDEAS for generating a I DEAS universal file FORM FEMAP for generating a FEMAP neutral file FORM ANSYS for generating a ANSYS supported neutral file FORM NASTRAN for generating a NASTRAN bulk data deck FORM NASTL for generating a NASTRAN bulk data deck with GRID entries in large field format 1 allows for higher degree of numerical accuracy over the FORM NASTRAN option Character string up to 16 characters to specify the filename to store the surface boxes and CFD grid point for plotting If the first character starts with a dollar sign the rest of the characters must be integers This integ
145. 58403E 02 4 60747E 02 0 00000E 00 10102 G 0 00000E 00 0 00000E 00 1 01415 02 6 32742E 04 6 43032E 04 0 00000E 00 10103 G 0 00000E 00 0 00000E 00 5 49054E 01 3 57703E 02 3 07092E 02 0 00000E 00 10104 G 0 00000E 00 0 00000E 00 1 00000E 00 7 20460E 02 2 40956E 03 0 00000E 00 10201 G 0 00000E 00 0 00000 00 6 66242 01 2 65721 02 1 53368E 02 0 00000E 00 10202 G 0 00000E 00 0 00000E 00 2 27467 01 1 97661E 02 1 47552E 02 0 00000E 00 10203 G 0 00000E 00 0 00000E 00 7 48511 02 1 81559E 02 5 30764E 03 0 00000E 00 10204 G 0 00000E 00 0 00000E 00 4 51465E 01 4 65767E 02 2 02751E 02 0 00000E 00 10301 G 0 00000E 00 0 00000E 00 4 88703E 01 9 74488E 03 2 84319E 02 0 00000E 00 10302 G 0 00000E 00 0 00000E 00 4 13593E 02 2 35718 02 1 00285E 02 0 00000E 00 10303 G 0 00000E 00 0 00000E 00 1 31374 01 1 94000E 02 1 94331E 02 0 00000E 00 10304 G 0 00000E 00 0 00000E 00 8 59769 01 1 16691E 02 4 44581E 02 0 00000E 00 10401 G 0 00000E 00 0 00000E 00 7 68068E 01 5 36557E 02 2 24129E 02 0 00000E 00 10402 G 0 00000E 00 0 00000E 00 9 32998E 01 5 02390E 02 4 81151E 03 0 00000E 00 10403 G 0 00000E 00 0 00000E 00 6 32223E 01 5 15985E 02 3 23634E 02 0 00000E 00 10404 G 0 00000E 00 0 00000E 00 4 26008E 02 5 12637E 02 4 69097E 02 0 00000E 00 20000 G 0 00000E 00 0 00000E 00 0 00000E 00 0 00000E 00 0 00000E 00 0 00000E 00 Remark 6 of ASSIGN FEM If FORM IDEAS the structural grids and modal results are read in from I DEAS universal file
146. 8 02 0 00000E 00 10103 0 00000E 00 0 00000E 00 0 75844E 00 0 20153 01 0 42887 01 0 00000E 00 10104 0 00000E 00 0 00000E 00 0 20276E 01 0 30486E 01 0 32503 01 0 00000E 00 10201 0 00000E 00 0 00000E 00 0 61311E 00 0 18695E 01 0 79740 02 0 00000E 00 10202 0 00000E 00 0 00000E 00 0 22314E 00 0 27600E 01 0 19683E 01 0 00000E 00 10203 0 00000E 00 0 00000E 00 0 42123E 00 0 25182E 01 0 25962 01 0 00000E 00 10204 0 00000E 00 0 00000E 00 0 13023E 01 0 31480 01 0 36780 01 0 00000E 00 10301 0 00000E 00 0 00000E 00 0 10832E 01 0 35884E 01 0 13684 01 0 00000E 00 10302 0 00000E 00 0 00000E 00 0 69096E 00 0 31485E 01 0 21684 01 0 00000E 00 10303 0 00000E 00 0 00000E 00 0 13155E 00 0 34301E 01 0 28107 01 0 00000E 00 10304 0 00000E 00 0 00000E 00 0 51537E 00 0 35056E 01 0 29567 01 0 00000E 00 10401 0 00000E 00 0 00000E 00 0 16244E 01 0 35439E 01 0 21997 01 0 00000E 00 10402 0 00000E 00 0 00000E 00 0 12405E 01 0 37052E 01 0 24214 01 0 00000E 00 10403 0 00000E 00 0 00000E 00 0 80819E 00 0 36387E 01 0 27230 01 0 00000E 00 10404 0 00000E 00 0 00000E 00 0 33566E 00 0 37273E 01 0 28986 01 0 00000E 00 20000 0 00000E 00 0 00000E 00 0 00000E 00 0 00000E 00 0 00000E 00 0 00000E 00 MODE 3 0 20776E 03 0 10000E 01 10101 0 00000E 00 0 00000E 00 0 85853E 00 0 47730E 01 0 45322E 01 0 00000E 00 10102 0 00000E 00 0 00000E 00 0 40923E 01 0 22853E 02 0 10635 02 0 00000E 00 10103 0 00000E 00 0 00000E 00 0 66112E 00 0 334
147. 8076 02 1 82668E 02 0 00000E 00 10301 G 0 00000E 00 0 00000E 00 5 32187 01 1 78486 02 6 38841E 03 0 00000E 00 10302 G 0 00000E 00 0 00000E 00 3 44961 01 1 56378E 02 1 04377E 02 0 00000E 00 10303 G 0 00000E 00 0 00000E 00 7 43806 02 1 71329E 02 1 37092E 02 0 00000E 00 10304 G 0 00000E 00 0 00000E 00 2 41691E 01 1 75982E 02 1 45025E 02 0 00000E 00 10401 G 0 00000E 00 0 00000E 00 8 07570 01 1 76693E 02 1 05283E 02 0 00000E 00 10402 G 0 00000E 00 0 00000 00 6 22996 01 1 85493 02 1 16236E 02 0 00000E 00 10403 G 0 00000E 00 0 00000E 00 4 14728 01 1 82571 02 1 31904E 02 0 00000E 00 10404 G 0 00000E 00 0 00000E 00 1 85288 01 1 87568 02 1 41208E 02 0 00000E 00 20000 G 0 00000E 00 0 00000E 00 0 00000E 00 0 00000E 00 0 00000E 00 0 00000E 00 ASTROS VERSION 21 2 B04 10 09 P 10 FINAL ANALYSIS SEGMENT DEMO CASE MODES ANALYSIS BOUNDARY 1 MODE 3 REAL EIGENVECTOR FOR MODE 3 EIGENVALUE 3 41514E 04 RAD S 2 CYCLIC FREQUENCY 2 94120E 01 HZ POINT ID TYPE TI T2 T3 R1 R2 R3 10101 G 0 00000E 00 0 00000E 00 1 75601 01 2 32465E 02 9 02655E 03 0 00000E 00 10102 G 0 00000E 00 0 00000E 00 1 71048 02 9 66031 04 6 84568 04 0 00000E 00 10103 G 0 00000E 00 0 00000E 00 2 88296 01 1 42254E 03 1 34849E 02 0 00000E 00 10104 G 0 00000E 00 0 00000E 00 6 34242 01 2 18125E 02 6 83909E 03 0 00000E 00 10201 G 0 00000E 00 0 00000 00 4 50809 01 1 25424 02 1 14398E 02 0 00000E 00 10202 G 0 00000E 00 0 0000
148. 9 10 CAEROCP CID IDWING IYS IYE IXS IXE CPU CPL Field Contents CID Identification number Integer gt 0 See Remark 1 IDWING Identification number of a CAERO7 bulk data card Integer gt 0 IYS The starting strip index Integer gt 0 IYE The ending strip index Integer gt 0 IXS The starting chordwise panel index Integer gt 0 IXE The ending chordwise panel index Integer gt 0 See Remark 2 CPU A factor applied to the upper surface pressure coefficients Real default 1 0 CPL A factor applied to the lower surface pressure coefficients Real default 1 0 Remarks 1 Multiple CAEROCP bulk data cards can be specified to apply factors to various CAERO7 macroelements 2 Only the pressure coefficients on those within IYS IYE IXS and IXE are multiplied by the factor specified in the CPU and CPL entries IYS 4 52 DATA DESCRIPTION CBAR CBAR Wake Element Description Defines a flat wake surface by specifying two surface grid points Format and Example 1 2 3 4 5 6 7 8 9 10 CBAR EID PBAR GA GB 2 CONT CONT PA PB CBAR 2 101 131 C 0 100 Field Contents EID Identification number Integer gt 0 See Remark 1 PBAR Not used GA GB Identification numbers of two GRID bulk data cards GA and GB must be the surface grid points PS 0 in the GRID bulk data card Integer gt 0 See Remark 2
149. 9 26337 02 1 47431 02 0 00000E 00 0 00000E 00 12 12 1 03264 06 1 01619 03 1 61732 02 0 00000E 00 0 00000E 00 13 13 1 17125 06 1 08224 03 1 72245 02 0 00000E 00 0 00000E 00 14 14 1 76139E 06 1 32717E 03 2 11226E 02 0 00000E 00 0 00000E 00 15 15 2 78933 06 1 67013E 03 2 65809E 02 0 00000E 00 0 00000E 00 16 16 4 13498E 06 2 03347 03 3 23636 02 0 00000E 00 0 00000E 00 d ASTROS VERSION 21 2 B04 10 09 P 8 FINAL ANALYSIS SEGMENT DEMO CASE MODES ANALYSIS BOUNDARY 1 MODE 1 REAL EIGENVECTOR FOR MODE t EIGENVALUE 7 85673E 02 RAD S 2 CYCLIC FREQUENCY 4 46109E 00 HZ POINT ID TYPE Tl T2 T3 R1 R2 R3 10101 G 0 00000E 00 0 00000E 00 1 57724 01 4 74973E 04 9 04594E 03 0 00000E 00 10102 G 0 00000E 00 0 00000E 00 1 65129E 03 1 01365E 04 4 18610 04 0 00000E 00 10103 G 0 00000E 00 0 00000E 00 1 60828E 01 7 84750E 03 8 90299E 03 0 00000E 00 3 10 EXECUTIVE CONTROL SECTION ASSIGN FEM 10104 G 0 00000E 00 0 00000E 00 4 75673E 01 7 20763E 03 9 88694E 03 0 00000E 00 10201 G 0 00000E 00 0 00000E 00 3 11719 02 1 54758E 03 3 01484E 03 0 00000E 00 10202 G 0 00000E 00 0 00000E 00 1 30878E 01 6 42130E 03 8 59521E 03 0 00000E 00 10203 G 0 00000E 00 0 00000E 00 3 82162 01 6 65170 03 9 26838E 03 0 00000E 00 10204 G 0 00000E 00 0 00000E 00 6 49799E 01 7 61182E 03 9 90462E 03 0 00000E 00 10301 G 0 00000E 00 0 00000E 00 1 69017E 01 6 16125E 03 9 91356E 03 0 00000E 00 10302 G 0 00000E 00 0 00000E 00 3 84447E 01 6
150. 9E 03 068093E 03 145165E 02 657062E 02 839550E 02 879387E 02 529658E 02 219073E 02 048384E 02 970822E 02 613626E 02 0 R2 266406E 01 314526E 03 121695E 02 096157E 02 163387E 02 Ooooooooooooooooo oOooooooooooooooo Ooooooooooooooooo oOooooooooooooooo 0 Ooooooooooooooooo ooooo Ooooooooooooooooo ooooo GENERALIZED S Mo oS UD R3 R3 R3 R3 TIFFNESS 399865 02 401589 03 316370 04 341672 04 008154 05 3 8 EXECUTIVE CONTROL SECTION ASSIGN FEM 10202 G 0 0 0 0 1 576902E 01 9 684119E 04 10203 G 0 0 0 0 2 870014 01 6 443665E 03 10204 G 0 0 0 0 4 325946E 01 2 493853E 02 10301 G 0 0 0 0 2 637444E 01 3 015133E 02 10302 G 0 0 0 0 4 917885E 01 1 411954E 02 10303 G 0 0 0 0 9 593081 03 4 840639 03 10304 G 0 0 0 0 9 164144E 01 1 701009E 02 10401 G 0 0 0 0 9 870760E 01 2 619092 02 10402 G 0 0 0 0 5 199889E 01 9 901542E 03 10403 G 0 0 0 0 2 610622 01 8 370100 04 10404 G 0 0 0 0 1 179375E 00 7 177794E 03 20000 G 0 0 0 0 0 0 0 0 EIGENVALUE 2 008154 05 CYCLES 7 132120E 01 REAL EIGENVECTOR NO POINT ID TYPE Tl T2 T3 R1 10101 G 0 0 0 0 1 976632E 00 9 472703E 02 10102 G 0 0 0 0 2 276870E 02 1 390012 03 10103 G 0 0 0 0 8 776556E 01 7 974713E 02 10104 G 0 0 0 0 2 455836E 00 1 372054E 01 10201 G 0 0 0 0 7 512134E 01 4 105826E 02 10202 G 0 0 0 0 6 829810E 01 3 796132 02 10203 G 0 0 0 0 5 347021E 01 3 837091E 0
151. A ID 102 BULK DATA DESCRIPTION PSHELL PSHELL Property of the CQUAD4 CTRIAS3 Panels Description Specifies the property of the COUADA CTRIA3 Panels Format and Example T 2 3 4 5 6 7 8 9 10 PSHELL MID1 INCLINE FLOWIN ITYPE IPFOR CPFACT CONT Field PID MIDI EPS INCLINE FLOWIN ITYPE IPFOR CPFACT XOFF YOFF ZOFF Contents Unique identification number Integer gt 0 See Remark 1 Identification number of a MATBODY bulk data card Integer gt 0 Tolerance to detect the skewness of the panel Real Default 0 0001 Flag for Superinclined panel and active only for Mach number gt 1 Incline 0 not Superinclined panel Incline 0 Superinclined panel Integer gt 0 See Remark 2 Amount of flow in percentage of the flow contained in the stream tube in front of engine inlet or behind engine nozzle the panel which penetrates into out to the panel FLOWIN 100 implies that 100 of the flow penetrates into out the panel Real 0 0 lt FLOWIN x 100 0 ITYPE 0 panel boundary condition depends on the flight condition f q ITYPE 1 panel is used to model the wind tunnel walls or ground where a f p q r 0 0 Integer Flag for pressure formula to compute the pressure coefficients IPFOR 0 Exact isentropic C formula IPFOR 1 C 2 u 1 MZ IPFOR 2 2 where and are the perturbation velocity components Intege
152. AS FEMAP ANSYS NASTRAN Static Aeroelastic Trim Analysis Results PLTTRIM Generates an ASCII text file for the post processing of the static aeroelastic trim analysis PATRAN TECPLOT I DEAS FEMAP ANSYS NASTRAN PEGASUS output plot files are saved in ASCII text format can be directly read in by the graphical software programs listed in the above table or any equivalent software packages that can process the same data format The PATRAN output is a combination of neutral file containing the aerodynamic model and results file PLOT FILES 17 1 containing the displacement or pressure results output Note that for the PATRAN output option the aerodynamic models generated by the PL Txxxx bulk data cards all stored in neutral file format are all different from one another and cannot be used interchangeably This restriction is due to the necessity of duplicating grid points in some of the output plot files to allow for viewing or animation of discontinuous components e g a flapping control surface in a modal analysis addition some plot files like PLTMODE require displaying of both sides of the model even though only half of the model may have been specified in the input For this reason the user must take extra care when requesting multiple plot files in PATRAN format to ensure that the aerodynamic model names are unique or they will be overwritten T
153. ASCII text file for IDEAS PLTCP plotting the unsteady pressure FEMAP coefficients ANSYS NASTRAN PEGASUS PATRAN TECPLOT Generates an ASCII text file for DEAS PLTMODE plotting the interpolated structural mode on the aerodynamic model Aerodynamic Model PLTAERO Aerodynamic Pressure Coefficients Interpolated Structural Modes FEMAP ANSYS NASTRAN PATRAN TECPLOT I DEAS FEMAP ANSYS NASTRAN PATRAN TECPLOT Generates an ASCII text file for the DEAS PLTTRIM post processing of the static FEMAP aeroelastic trim analysis ANSYS NASTRAN PEGASUS ASCII text file generation for PLTSURF plotting the aerodynamic control surface Control Surface Deflection Static Aeroelastic Trim Analysis Results 2 6 How TO RUN ZONAIR 2 5 ZONAIR RESTART CAPABILITY The ZONAIR software system has an optional restart capability that reads the saved Aerodynamic Influence Coefficient AIC matrices generated during previous runs The AIC file is generated by specifying the SAVE option in the MACH bulk data card see MACH bulk data card in Section 4 The AIC file is saved in the same directory as the input and output decks and accordingly must be located in the same directory as the input deck during a restart run Since the generation of the AIC matrices almost always requires the longest time to complete any ZONAIR job the restart f
154. An AUTOTIP bulk data card is internally generated by the program to model the root or tip section of the thick wing component respectively See the description of the AUTOTIP bulk data card for details 4 176 DATA DESCRIPTION THKWING The surface grid points listed in the SET1 bulk data card defines the wing body junction so that the program can create a hole on the body All grid points around this hole on the body are connected to the grid points of the root section of the thick wing component In the figure shown below the surface grid points 201 107 303 and 404 are listed in the SET1 bulk data card The program will automatically move the locations of those grid points to the lower surface of the root section of the thick wing component The grid points on the upper surface of the root section are generated by the program Note that the size of the hole on the body is defined by the PAFOIL7 PAFOILS bulk data card Note that if LRCHD AUTO the number of surface grid points along the wing body junction must be equal to NCHORD Otherwise a fatal error occurs RWAKE entry is very similar to that of the CAERO7 bulk data card except an RBE2 bulk data card is internally generated by the program to account for such a potential jump across the wake sheet See the RWAKE entry of the CAERO7 bulk data card and the description of the RBE2 bulk data card CANTR determines the CANT angle of the hole
155. CONT LRCHD RWAKE CONT WID PSHELL ACOORD NSPAN NCHORD LSPAN PAFOIL7 AUTOTIP Contents Unique identification number Integer gt 0 See Remark 1 Identification number of a PSHELL bulk data card Integer gt 0 Identification number of ACOORD specifying a local coordinate system and orientation bulk data card Integer 0 or Blank Default 0 See Remark 2 Number of spanwise divisions of the thick wing component Integer 2 2 Number of chordwise divisions of the thick wing component Integer 2 2 Identification number of AEFACT bulk data card used to specify the spanwise divisions of the thick wing component in percentage of the wing span The number of values listed in AEFACT must be NSPAN and must start with 0 0 and end with 100 0 If LSPAN 0 then NSPAN evenly distributed spanwise divisions are used Integer 2 0 See Remark 3 Identification number of a PAFOIL7 PAFOILS bulk data card to specify sectional airfoil coordinates Integer gt 0 Character either BOTH ROOT or NONE AUTOTIP BOTH TIP modeling is performed for both the root and tip sections AUTOTIP ROOT TIP modeling is performed for the root section AUTOTIP TIP a TIP modeling is performed for the tip section AUTOTIP NONE TIP modeling Character Default NONE See Remark 4 4 174 DATA DESCRIPTION THKWING
156. CORD2C CID RID Al A2 A3 B1 B2 B3 CONT CONT C1 C2 C3 CORD2C 3 17 2 9 1 0 0 0 3 6 0 0 L40 23 23 52 1 0 S2 9 Field Contents CID Coordinate system identification number Integer gt 0 RID Reference to a coordinate system which is defined independently of new coordinate system Integer 2 0 or blank Ai Bi Ci Coordinates of three points in coordinate system defined by RID Real x Remarks 1 A continuation entry must be present 2 The three points Al A2 A3 B2 B3 C2 C3 must be unique and noncollinear Noncollinearity 1s checked by the geometry processor 4 60 DATA DESCRIPTION CORD2C Coordinate system identification numbers on all CORDIR CORDIC CORDIS CORD2R CORD2C and CORD2S entries must all be unique An RID of zero references the basic coordinate system The location of a grid point P in the sketch in this coordinate system is given by R 0 Z where 0 is measured in degrees The displacement coordinate directions at P are dependent on the location of P as shown above by u ue uz Points on the z axis may not have their displacement directions defined in this coordinate system since an ambiguity results BULK DATA DESCRIPTION 4 61 CORD2R CORD2R Rectangular Coordinate System Definition Form 2 Description Defines a rectangular coordinate system by reference to coordinates of three points The first point defines the origin The second point defines the direct
157. D Elements Along Wing Tip for Vortex Roll Up A linear vortex singularity is distributed along each of the line vortex segments The strength of the vortex singularity is determined by the doublet strength at those grid points to which those line vortex segments are attached Behind the trailing edge of the wing tip the roll up vortex is modeled by two line vortex elements starting from the trailing edge and extending to infinity Figure 5 12 one line vortex element is attached to the grid points at the upper surface of the wing tip trailing edge and the other to the lower surface These infinite line vortex elements are specified in the CBAR bulk data card Similar to the flat wake model the infinite line vortex element is always parallel to the x axis of the aerodynamic coordinate system In fact without the infinite line vortex element a free edge occurs along the tip of the flat wake surface generated by the CBAR element which violates the closure condition This is to say that a free edge either along the tip of a wing or a wake surface must be terminated by a line vortex element The potential jump due to the line vortex element is computed by the difference in vortex strength of the line vortex at the upper and the lower surfaces Infinite line vortex elements Figure 5 12 Infinite Line Vortex Elements to Model the Roll Up Vortex Behind the Wing Trailing Edge However the line vortex modeling for the roll up vortex is applicable only f
158. DA entry defines the angle of the ith wake line at the trailing edge of the thick wing If GRIDA 0 GRIDA is the identification number of a reference grid input by the GRID bulk data card with entry PS z 0 to specify a vector from GRIDU GRIDL to see the following figure This vector defines the direction of the ith wake line at the trailing edge of the thick wing component Average postion between e Reference grid with ID GRIDA For GRIDA 0 or blank the direction of the ith wake line at the trailing edge of the thick wing component is automatically computed by the average value of the tangential vectors of the panels to which the GRIDU and GRIDL are attached see the figure below BULK DATA DESCRIPTION 4 213 WAKENET 10 4 214 Tangential vector of the upper panel i Pi Direction of the ith wake line Tangential vector of the lower panel The user must assign a proper GRIDREF to avoid duplicated identification numbers of the reference grid points The streamwise location where the direction of the ith wake line defined by SLOPE is imposed is shown in the following example LENGTH CNTLX lt a i 100 The locations of these reference grids ahead of CNTLX at j 1 2 and 3 shown in the figure are determined by a two point cubic spline with imposed slopes at LENGTH and at the trailing 100 edge of the thick wing component The locations o
159. Drag Coefficient Dis drag force qa REFS Pitch Moment Coefficient C M Mis the pitch moment 2 REFS REFC Side Force Coefficient E Y Y is the side force Y q REFS Roll Moment Coefficient isthe roll moment 4 REFS REFB Yaw Moment Coefficient C N Nis the yaw moment q REFS REFB Note that all forces and moments computed by the program account for those generated by both sides of the configuration even if only a right hand side configuration is modeled Therefore REFS should account for the area on both sides of the configuration aerodynamic moment coefficients as well as stability derivatives are computed using REFX REFY and REFZ as the aerodynamic moment center BULK DATA DESCRIPTION 4 23 AESLINK AESLINK Aerodynamic Control Surface Linking Description Defines an additional aerodynamic control surface by linking a set of AESURFZ bulk data cards Format and Example 1 2 3 4 5 6 7 8 9 10 AESLINK LABEL TYPE ACTID CONT CONT COEFF1 AESURF1 COEFF2 AESURF2 AESLINK AES1 SYM 100 A A 52 0 AES2 0 5 AES3 0 3 AES4 Field Contents LABEL Unique alphanumeric string of up to eight characters used to define an additional aerodynamic control surface Character See Remark 1 TYPE Type of boundary condition Character See Remark 2 SYM symmetric ANTI anti
160. E VARIABLE X Y Z EXTID ZONE I J F FEPOINT lists the number of aerodynamic grids structural finite element grids and aerodynamic panels defines the variable names associated with the column data X coordinate of the aerodynamic grid point Y coordinate of the aerodynamic grid point Z coordinate of the aerodynamic grid point External grid point identification number specifies information for the current zone the Tecplot input can be broken up into multiple zones only one ZONE is used to define the aerodynamic model number of aerodynamic grid points listed in the plot file number of aerodynamic panels listed in the plot file finite element zone specification 7 4 PLOT FILES e DEAS Compatible Output The I DEAS compatible output is saved in the universal file format Data set 781 is used to output the aerodynamic as well as structural if requested in the PLTAERO bulk data card grid points Data set 780 is used to output the aerodynamic panels A sample of the I DEAS compatible output is shown in the following figure 781 201 0 0 11 1 0000000000000000D 02 0 0000000000000000D 00 0 0000000000000000D 00 202 0 0 11 1 0000000000000000D 02 0 0000000000000000D 00 0 0000000000000000D 00 203 0 0 TT 1 0000000000000000D 02 0 0000000000000000D 00 0 0000000000000000D 00 204 0 0 TI 1 0000000000000000D 02 0 0000000000000 0D 00 0 0000000000000000D 00 d Aerodynamic Grid Points 101 0 0 Tr 0 000000000
161. E 04 3 34307E 03 0 00000E 00 10104 G 0 00000E 00 0 00000E 00 1 42218E 02 4 72348E 03 8 03788E 03 0 00000E 00 10201 G 0 00000E 00 0 00000E 00 2 91175 01 7 87643E 03 1 41986E 02 0 00000E 00 10202 G 0 00000E 00 0 00000E 00 2 42111 02 8 48906E 04 6 83955E 03 0 00000E 00 10203 G 0 00000E 00 0 00000E 00 4 72883E 02 7 89466E 04 5 12644E 03 0 00000E 00 10204 G 0 00000E 00 0 00000E 00 1 03009E 01 2 83089E 03 5 22758E 03 0 00000E 00 10301 G 0 00000E 00 0 00000 00 1 28856 02 4 00481E 03 4 67938E 03 0 00000E 00 10302 G 0 00000E 00 0 00000E 00 6 90750 02 1 66587 03 9 81907E 04 0 00000E 00 10303 G 0 00000E 00 0 00000E 00 2 46962 04 9 49519E 04 5 16162E 03 0 00000E 00 10304 G 0 00000E 00 0 00000E 00 1 50640E 01 1 48197E 03 7 97554E 03 0 00000E 00 10401 G 0 00000E 00 0 00000E 00 1 25005E 01 3 45775 03 2 60315E 03 0 00000E 00 10402 G 0 00000E 00 0 00000E 00 6 85205 02 9 94270 04 5 30369E 03 0 00000E 00 10403 G 0 00000E 00 0 00000E 00 3 93305E 02 3 41754 04 7 56189E 03 0 00000E 00 10404 G 0 00000E 00 0 00000E 00 1 70948E 01 5 85900E 04 7 80940E 03 0 00000E 00 20000 G 0 00000E 00 0 00000E 00 0 00000E 00 0 00000E 00 0 00000E 00 0 00000E 00 1 ASTROS VERSION 21 2 B04 10 09 P 12 FINAL ANALYSIS SEGMENT DEMO CASE MODES ANALYSIS BOUNDARY 1 MODE 5 REAL EIGENVECTOR FOR MODE 5 EIGENVALUE 9 88844 04 RAD S 2 CYCLIC FREQUENCY 5 00477E 01 HZ POINT ID TYPE T1 T2 T3 R1 R2 R3 10101 G 0 00000E 00 0 00000E 00 7 30464E 01 6
162. EID The objective of the VORNET bulk data card is to model a vortex roll up sheet on the wing leading edge or top of the body See figures below TIPGRID d Vorticity feeding sheet i Vorticity feeding sheet i Vortex core line y 9 Vortex core line where the CROD where the CROD elements are elements are located located set of reference grid points 5 gt 0 in the GRID bulk data card are internally generated and located along the vortex core line These reference grid points the entry IDSETi in the VORNET bulk data card See the remarks of the VORNET bulk data card for the description of ROLLUP and NFED The initial vector is shown in the figure below The search vector slices the surface grid into two sets of surface grid points from TIPGRID to the end of the body or trailing edge of the wing These two set of surface grid points are the input to the entries GRIDU and GRIDLi of the VORNET bulk data card Note that if GRID lt 0 the program automatically sets GRIDU GRIDLi where i is the index of the end point with ID ABS GRID BULK DATA DESCRIPTION 4 39 AUTPVOR Initial search vector TIPGRID nS Initial search vector lt GRID GRID BULK DATA DESCRIPTION 4 40 BODY7 BODY7 Aerodynamic Body Component Description Defines an aerodynamic body macroelement of a body like component Format and Example
163. EVERSE Character string either Yes or No For REVERSE YES the resulting airfoil shape of the upper and lower surface is reversed Character Default NO See Remark 2 Remarks 1 PAFOILS bulk data card is an alternative form of the PAFOIL7 bulk data card If the ZONA7U or ZTRAN unsteady aerodynamic method is activated see the METHOD entry in the MKAEROZ bulk data card one of the PAFOIL7 and PAFOILS bulk data card must be referred to by the CAERO7 bulk data card 2 If the CAERO7 macroelement is located the left hand side and is modeled from the wing root to wing tip the airfoil shape must be upside down to follow the normal vector convention of the CAERO7 bulk data card See Remark 5 of the CAERO7 bulk data card In this case REVERSE YES must be used 4 132 DATA DESCRIPTION PANLSTI PANLST1 Set of Aerodynamic Panels Description Defines a set of aerodynamic thin wing panels that are generated by the CAERO7 bulk data card Format and Example 1 2 3 4 5 6 8 9 10 mum Field Contents SETID Unique set identification number Integer gt 0 See Remark 1 MACROID Identification number of a CAERO7 bulk data card to which the aerodynamic panels listed in the set belongs Integer 0 See Remark 2 PANELI Identification number of the first aerodynamic thin wing panel Integer gt 0 PANEL2 Identification number of the last aerodynamic thin wing pan
164. G DMI bulk data card or MNAME of ASSIGN MATRIX Executive Control Command This matrix is used as the elementary stiffness matrix of the design variable with value of THICKi Character BULK DATA DESCRIPTION 4 195 TRIMSEN Remarks 1 is used for error message output only 2 The TRIMSEN bulk data card refers to a TRIM Case Control Command by the entry IDFLT One TRIMSEN bulk data card can specify multiple design variables The derivatives of the trim responses with respect to the unit value of each design variable will be computed as the sensitivity analysis These trim responses are specified in the TRIMFNC bulk data cards that are referred to by the TRIM bulk data card through a SET1 bulk data card 3 It 1s assumed that the elementary mass and stiffness matrices are linearly varying with respect to the design variables Therefore the derivatives of the total mass and stiffness matrices can be obtained by dividing MASS and STIFFi by THICK Specifically the derivatives of the total mass Mog and stiffness matrices defined at the Structural g set degrees of freedom with respect to V are 9M _ MASSi STIFFi 9V THICKi THICKi i where V represents the i design variable 4 196 DATA DESCRIPTION TRIMVAR TRIMVAR Trim Variable Bulk Data Card Description Defines a trim variable for the static aeroelastic trim analysis Format and Example 1 2 3 4 5 6 Y 8 9 10 TRIMVAR
165. IEND gt ISTART gt 0 JEND gt START gt 0 and KEND gt KSTART gt 0 Integer gt 0 See Remark 3 1 The OMITCFD bulk data card is referred to by an INPCFD bulk data card Because ZONAIR only requires the CFD solution on the surface mesh to replace the program computed pressure coefficients by the CFD solution specifying the surface mesh index can avoid the reading of all CFD grid points into the computer memory 2 The objective of the FILEMESH entries is to output a graphical file that allows the user to verify the overlapping between the ZONAIR surface boxes and those CFD grid points near the surface mesh 3 The CFD grid points defined by BLOCKi ISTARTi IENDi JSTARTi JENDi KSTARTi and KENDi are the CFD surface mesh BULK DATA DESCRIPTION 4 125 OMITMOD OMITMOD Delete Structural Modes Description Delete structural modes from the database permanently Format and a Field Contents SYMM Character string to specify the boundary condition of which the structural modes are to be deleted SYMM SYM for symmetric modes SYMM ANTI for anti symmetric modes SYMM ASYM for asymmetric modes Character See Remark 1 MAXMOD All structural modes whose indices are greater than MAXMOD are deleted Note that if MAXMOD 0 no mode is deleted Integer gt 0 Default index of the highest mode MODEi Optional indices of the structural mode s that are to be deleted In addition to any
166. ION 4 35 AUTOTIP The AUTOTIP bulk data card automatically generates two sets of surface grid points The location of these surface grid points is the average of the location of those grid points listed in the SET1 bulk data cards with identification numbers being equal to UPSETI and LOWSET1 The identification numbers of those automatically generated surface grid points start from GRIDS In the example shown above six surface grid points are generated by the AUTOTIP bulk data card If GRIDS 101 the identification numbers of those grid points are 101 102 103 104 105 and 106 where grid points 101 102 and 103 are used to connect the upper part of the CQUAD4 CTRIAS elements and grid points 104 105 and 106 connect the lower part of the CQUAD4 CTRIA3 elements The AUTOTIP bulk data card automatically generated two sets of CQUAD4 CTRIA3 elements one connects to those surface grid points along the upper surface at the wing tip and the other one connects the lower surface The identification numbers of these automatically generated CQUAD4 CTRIA3 elements start from PANELS 302 301 305 304 308 306 308 307 In the example shown above eight CQUAD4 CTRIA3 elements are automatically generated by the AUTOTIP bulk data card If PANELS 301 the identification numbers of those COUADA CTRIA3 elements are 301 308 where elements 301 304 are connected to the upper grid points and the elements 305 308 to the lo
167. IPGRID UPSET1 LOWSET1 AUTOTIP 10 101 301 1 10 1001 20 0 Field Contents EID Unique identification number Integer gt 0 See Remark 1 GRIDS Starting identification number of those internally generated grid points Integer gt 0 See Remark 2 PANELS Starting identification number of those internally generated CQUADA CTRIA3 elements Integer gt 0 See Remark 3 RODS Starting identification number of those internally generated CROD elements Integer gt 0 See Remark 4 PSHELL Identification number of a PSHELL bulk data card Integer gt 0 TIPGRID Identification number of a surface grid point that is located at the leading edge of the wing tip Integer gt 0 See Remark 5 UPSETI Identification number of a SET1 bulk data card that lists a set of identification numbers of surface grid points that are located along the upper surface of the wing tip Integer 2 0 See Remark 6 LOWSETI Identification number of a SET1 bulk data card that lists a set of identification numbers of surface grid points that are located along the lower surface of the wing tip Integer 2 0 See Remark 7 Remarks 1 purpose of AUTOTIP bulk data card is to automatically generate a set of surface grid points CQUAD4 CTRIA3 element and CROD element for the modeling of the tip of a thick wing component See the example below SS Thick wing without tip modeling Thick wing with the AUTOTIP bulk data card BULK DATA DESCRIPT
168. IR by the ASSIGN MATRIX Executive Control Command e The format for symmetric or asymmetric boundary condition is ASSIGN MATRIX demol mgh MNAME SMGH FORM FORMAT format for anti symmetric boundary condition is ASSIGN MATRIX demol mgh MNAME AMGH FORM FORMAT Note that the name of the matrix is defined as MGH in the NASTRAN DMAP alter statements However the ASSIGN MATRIX Executive Control Command for trim analysis it is replaced by MNAME SMGH for the symmetric boundary condition and MNAME for the anti symmetric boundary condition An alternative way to obtain the SMGH and or AMGH matrices is to import the MGG matrix directly This can be achieved by using the following Executive Control Command ASSIGN MATRIX filename MNAME MGG Once the MGG matrix is imported ZONAIR will automatically compute the SMGH and or AMGH matrices by multiplying the MGG matrix by the modal matrix CASE CONTROL SECTION 3 45 TRIM The following example shows the MSC NASTRAN DMAP alter statements that generate the MGG matrix ASSIGN OUTPUTA4 demol mgg UNIT 12 FORM FORMATTED SOL 103 COMPILE SEMODES SOUIN MSCSOU LIST NOREF 5 ALTER STRAIN ENGERGY MATGEN EQEXINS INTEXT 9 LUSETS GENERATE EXTERNAL SEQUENCE MATRIX MPYAD INTEXT MGG MGGT 1 TRANSFORM MGG TO EXTERNAL SEQUENCE OUTPUT4 MGGT 1 12 2 OUTPUT MGG UNIT 12 IN demol mgg ENDALTER CEND 3
169. K DATA DESCRIPTION 4 209 WAKENET DIVIDE IDAEF GRIDA GRIDREF LENGTH CNTLX Remarks Character string either SET1 COS or EVEN to define the streamwise location of reference grid points along the ith wake line Note that for DIVIDE 4 SETI NX number of reference grid points will be internally generated by the program Character default EVEN See Remark 6 For DIVIDE SETI IDAEF is the identification number of a SET1 bulk data card that lists a set of identification numbers of reference grid points defined by the GRID bulk data card with entry PS Z 0 However if i 1 the first wake line or i NY the last wake line list of identification numbers of surface grid points is also allowed Note that for DIVIDE SET1 the entries GRIDA GRIDREF LENGTH and CNTLX are not used See Remark 7 For DIVIDE IDAEF is the identification number of an AEFACT bulk data card that lists a set of real values to define the streamwise location of the reference grid points along the ith wake line For DIVIDE COS or EVEN is not used Identification number of a reference grid point to define the angle of the ith wake line at GRIDU and GRIDL For GRIDA 0 or blank the program will determine the angle using the average value of the streamwise tangential angles of the panels where GRIDU and GRIDL are attached Note
170. L DIVDE IDAEF GRIDA GRIDREF LENGTH CNTLX CONT CONT etc CONT CONT GRIDU GRIDLyy DIVIDEyy IDAEFyy GRIDAyy GRIDREFyy LENGTHg CNTLXyy WAKENET 101 WAKE 10 3 0 0 NONE CROD CBAR W W 104 106 EVEN 0 10 0 100 0 W W 234 239 COS 150 8 0 50 0 W W 107 207 SET1 10 103 10 0 90 0 Field Contents IDWAKE Identification number Integer gt 0 See Remark 1 LABEL An arbitrary character string used to define a label for the wake surface Character NX Number of points along the streamwise direction of each wake line Integer gt 0 NY Number of wake lines in the spanwise direction Integer gt 1 See Remark 2 SLOPE Slope in degrees specifying the angle of the wake at CNTLX Real See Remark 3 LINEI Character string either CBAR or NONE For LINEI CROD a set of elements is generated along the first wake line LINE CBAR a set of CBAR elements is generated along the first wake line LINE1 NONE nor CBAR is generated Character default NONE LINENY Same as LINEI but along the last wake line Character default NONE LINETE Same as LINE but along the trailing edge of the wake surface Character default CBAR See Remark 4 GRIDU Identification number of two surface grid points usually located on the upper and lower surface GRIDL at the trailing edge of a thick wing component where the ith wake line starts Integer See Remark 5 BUL
171. MOBJ TRIMOBJ Objective Function for the Static Aeroelastic Trim Analysis Description Defines an objective function to be minimized for solving the over determined trim system The objective function OBJ is defined as OBJ Y G4 5 8 Cu m ST where F is the value of a trim function Format and Example IDFNC 5114 El C2 82 E2 E CONT IDFNC C15 51 1 C2 52 E2 e cow sere lt i E ae ai Field Contents IDOBJ Unique Identification number Integer gt 0 See Remark 1 IDFNC Identification number of an TRIMFNC or TRIMADD bulk data card whose value is represented by the symbol F shown in the above equation Integer gt 0 Cl SI El Real coefficients shown in the above equation Real See Remark 2 2 52 2 Note Only E cannot be zero and E Remarks 1 IDOBJ is referred to by the TRIM bulk data card The TRIMOBJ bulk data card is active only for the over determined trim system The resulting objective function is the summary of a set of trim functions combined according to the equation shown above 2 Since C E S or E S could be negative the user must select proper value of E1 E2 and to avoid complex number resulting from the objective function 4 194 DATA DESCRIPTION TRIMSEN TRIMSEN Sensitivity Analysis Description Assigns a list of name of direct matrix input as design variables for Trim analysis Format and Examp
172. MPUTATIONAL TIME AND DISK SPACE REQUIREMENT Figure 5 24 gives ZONAIR computational time and disk space requirements as a function of the number of panels on a 2 4 Ghz PC computer It can be seen that the CPU time and disk space increase exponentially as the number of panels increase At 10 000 panels the disk space could require 20 GB and the CPU time could reach 800 minutes Therefore in order to keep the CPU time and disk space requirement on a reasonable level it is recommended that the number of panels be kept below 5 000 In fact numerical experience shows that a model with 5 000 panels is usually sufficient to model a complex configuration such as whole aircraft with external stores Beyond 5 000 panels the gain in accuracy may not be significant 900 25 000 800 20 000 700 amp 600 E o0 g 15 000 pg 5 gt 4 5 o9 10 000 300 a 200 5 000 100 0 i 7 7 i j o O 2 000 4 000 6 000 8 000 10 000 12 000 O 2 000 4 000 6 000 8 000 10 000 12 000 Panels Panels Figure 5 24 CPU Time and Disk Space Versus Number of Panels 5 14 GUIDELINES FOR AERODYNAMIC MODELING Chapter 6 MODELING GUIDELINES OF SPLINE FOR FLEXIBLE LOADS To compute the flexible loads due to the structural deformation it is required the coupling between the aerodynamics and structures Since the requirements to generate the discretized models for the structural analysi
173. N Case Control Command must appear within subcase section i e between two SUBCASE Case Control Commands 2 The integer n is the identification number of the AEROGEN bulk data card Integer gt 0 This AEROGEN bulk data card must exist in the Bulk Data Section 3 AEROGEN and n must be separated by an equal sign CASE CONTROL SECTION 3 35 BEGIN BULK BEGIN BULK The End of the Case Control Section Description signify the end of the Case Control Section and the beginning of the Bulk Data Section Format BEGIN BULK Example BEGIN BULK Remarks BEGIN BULK must be located at the end of the Case Control Section 3 36 CASE CONTROL SECTION ECHO ECHO Controls Echo of the Bulk Data Section Description Controls the echo printout of the Bulk Data Section Format NONE ECHO SORT NOSORT Example ECHO NOSORT Remarks 1 ECHO NONE no print ECHO SORT print out bulk data input cards in alphanumeric order ECHO NOSORT print out the unsorted bulk data input cards 2 If no ECHO is specified ECHO NONE is used 3 ECHO must appear before any SUBCASE Case Control Command 4 No more than one ECHO is allowed 5 The equal sign is required CASE CONTROL SECTION 3 37 GENBASE GENBASE Generates an Aerodynamic Database Description Generates an aerodynamic database by referring to a GENBASE bulk data card Format GENBASE N Example 1 GENBASE 100
174. ORATE PRATE STABDRV CONT CONT LABEL VALUE LABEL VALUE etc AEROGEN 100 10 1 0 0 0 0 01 0 0 0 0 YES A A RUDDER 1 0 ELEV 3 0 FLAP Field Contents IDAERO Identification number Integer gt 0 See Remark 1 IDMACH Identification number of a MACH bulk data card for defining the Mach number Integer gt 0 ALPHA Angle of attack in degrees Real BETA Side slip angle in degrees Real PRATE Non dimensional Roll Pitch and Yaw rates Real See Remark 2 QRATE RRATE STABDRV Character string either YES or NO For STABDRV YES the aerodynamic stability derivatives are computed Character Default NO See Remark 3 LABEL Label of the control surfaces defined in the AESURFZ AESLINK PZTMODE or JETFRC bulk data card Character VALUE Command to the control surfaces Real See Remark 4 Remarks 1 The AEROGEN bulk data card is referred to by an AEROGEN Case Control Command that invokes the program to compute the aerodynamic pressure coefficients forces and moments It also can be referred to by a TRIM GENBASE or FLEXLD bulk data card to define the flight condition where the aerodynamic loads are computed It should be noted that the rigid aerodynamic solution generated by the AEROGEN bulk data card can be replaced by the user supplied values using an INPCFD INPCFD1 INPDMI or CPSPLN bulk data card 4 20 DATA DESCRIPTION AEROGEN In additional to
175. PTION WTIFRC please refer to the WT1AJJ bulk data card for the description of the above equation If the given set of component forces and moments specified in the entries RFORCEI and RFORCE2 are obtained by wind tunnel test the dynamic pressure q at the wind tunnel test condition must be given to the above equation The entries Al RFORCEI A2 and RFORCE2 jointly define the given ith component forces moments derivative Fgiven as Fiven Al RFORCEl A2 RFORCE2 For instance if RFORCEI and RFORCE2 are the hinge moments of a control surface at angles of attack a 1 and 0 respectively Al should be 180 and A2 should be 180 z so that _ 180 given 2 07 Thus the resulting is the derivative of the hinge moment with respect to a pitch mode with a unit pitch angle BULK DATA DESCRIPTION 4 219 WT2AJJ WT2AJJ Downwash Weighting Matrix Description Corrects the aerodynamic influence coefficient AIC matrix by a downwash weighting matrix that is computed based on the given set of pressure coefficients Format and Example 10 1 2 3 4 5 6 7 8 9 WT2AJJ IDMK TYPE LABEL KINDEX METHOD WT2FILE FORM INPCFD1 INPCFD2 PLTCP CPFILE CONT pannen rantsr pameta ete WI2AJJ 100 SYM RIGID PITCH WT2FILE DAT W W CFD 57 1 101 EEG 102 TECPLOT CPL PLT W W 10 20 30 Field
176. R must be a negative integer in this case IDCOR 50 to flip the wind tunnel model from the negative y axis to the positive y axis 3 The wind tunnel data is stored in the free format If there are n numbers of wind tunnel measured pressure coefficients the format of the wind tunnel data is shown as follows ID X Yi Zi CP ID Xa Y 22 IDn Xn Mas Zw where ID is the identification number of the wind tunnel pressure that is referred to by the entry SETG Among all ID no duplicate ID is allowed Integer gt 0 X and Z are the location of the ith wind tunnel pressure Real is the ith measured pressure coefficient Real 4 68 BULK DATA DESCRIPTION CPSPLN Note that command cards may be used that must be initiated with in the first column An example of the file is shown as follows CP ON WING UPPER SURFACE 101 3 8066 2 1429 0 1530 0 0474 91 33 9695 19 2857 0 1750 0 0149 1008 33 0853 23 5714 0 3074 0 0941 CP ON WING LOWER SURFACE 100 37 6840 23 5714 0 1642 0 0125 200 39 9833 23 5714 0 0559 0 0428 98 43 5455 27 8571 0 0522 0 0549 TECPLOT FEMAP and I DEAS are commercially available graphical software programs I DEAS universal file output are data sets 781 and 780 for aerodynamic grids and aerodynamic boxes respectively PATRAN is the pres and post processor of NASTRAN FEMAP neutral file outputs are Data Blocks 403 and 404 for aerodynamic grids and
177. REAL EIGENVALUE SOLUTION MODE SHAPE 1 FREQUENCY HERTZ 4 61271E 000 1 2 3 8 2 6 L 0 1 0 1 al 0 0 1500 0 0 00000E 00 4 61271E 00 0 00000E 00 1 00000E 00 0 00000E 00 0 00000E 00 0 00000E 00 0 00000E 00 0 00000E 00 0 00000E 00 0 00000E 00 0 00000E 00 10101 0 00000E 00 0 00000E 00 2 43892E 01 1 38863E 02 1 04650E 03 0 00000E 0010102 0 00000E 00 0 00000E 00 2 68221E 03 6 51242E 04 1 64135E 04 0 00000E 0010103 0 00000E 00 0 00000E 00 2 53676E 01 1 38568E 02 1 23385E 02 0 00000E 0010104 0 00000E 00 0 00000E 00 7 42964E 01 1 52856E 02 1 12829E 02 0 00000E 0010201 EXECUTIVE CONTROL SECTION 3 13 ASSIGN FEM 0 00000 00 0 00000E 00 0 00000 00 0 00000E 00 0 00000 00 0 00000E 00 0 00000 00 0 00000E 00 0 00000 00 0 00000E 00 0 00000 00 0 00000E 00 0 00000 00 0 00000E 00 0 00000 00 0 00000E 00 0 00000 00 0 00000E 00 0 00000 00 0 00000E 00 0 00000 00 0 00000E 00 0 00000 00 0 00000E 00 0 00000E 00 0 00000E 00 1 552 6 aL a2 6 9 zl aF zs l 1 28180E 02 4 68218E 03 2 08856 01 1 33601E 02 1 01334 01 1 43458 02 1 01627 00 1 53258E 02 1 73692 01 1 53903E 02 9 08215E 01 1 45846E 02 1 46500E 01 1 54627E 02 1 29208E 00 1 54671E 02 1 74681E 01 1 54393E 02 1 03781 00 1 60022E 02 1 30443E 00 1 56486E 02 1 56637E 00 1 56380E 02 1 00000 00 0 00000E 00 0 Remark 7 of ASSIGN ZONAIR supports the ELFINI neutral output file to acquire the free vibrat
178. RID 10303 77 778 76 667 0 0 29 GRID 10304 100 000 76 667 0 0 30 GRID 10401 50 000 100 000 0 0 31 R GRID 10402 66 667 100 000 0 0 32 GRID 10403 83 333 100 000 0 0 33 GRID 10404 100 000 100 000 0 0 34 GRID 20000 33 333 0 0 0 0 3552 MATL 1100 1 07 23 zl 36 PBAR 1010 1100 100 1 04 1E 04 05 04 34 5 PSHELL 1000 1100 dub 1100 38 SPC 10 20000 123456 395 SPC1 10 126 10101 THRU 10104 40 SPC1 10 126 10201 THRU 10204 41 SPC1 10 126 10301 THRU 10304 42 SPC1 10 126 10401 THRU 10404 43 ENDDATA SUMMARY OF REAL EIGEN ANALYSIS 16 EIGENVALUES AND 5 EIGENVECTORS EXTRACTED USING METHOD MGIVENS MAXIMUM OFF DIAGONAL MASS TERM IS 1 890771509E 15 AT ROW 5 AND COLUMN 2 MODE EXTRACTION EIGENVALUE FREQUENCY GENERALIZED ORDER RAD S 2 RAD S HZ MASS STIFFNESS 1 alt 7 85673E 02 2 80299E 01 4 46109E 00 4 36633E 01 3 43051 02 2 2 4 40079E 03 6 63384E 01 1 05581E 01 3 02067E 01 1 32933E 03 3 3 3 41514E 04 1 84801E 02 2 94120E 01 2 70232E 01 9 22883 03 4 4 4 18786E 04 2 04643E 02 3 25699 01 9 05048 02 3 79021 03 5 5 9 88844 04 3 14459 02 5 00477 01 4 82244E 01 4 76864E 04 6 6 1 33059E 05 3 64773 02 5 80554 01 0 00000E 00 0 00000E 00 7 v 1 86616E 05 4 31991E 02 6 87535E 01 0 00000E 00 0 00000E 00 8 8 3 81747 05 6 17857 02 9 83350 01 0 00000E 00 0 00000E 00 9 9 3 88298E 05 6 23135 02 9 91751 01 0 00000E 00 0 00000E 00 10 10 6 67839 05 8 17214 02 1 30064 02 0 00000E 00 0 00000E 00 21 iX 8 58100E 05
179. RIDU GRIDL and GRID have negative sign In this case the segment between GRID and GRID or GRIDU GRIDL and GRID will not have the CBAR elements 4 158 DATA DESCRIPTION RELAXW RELAXW Wake Relaxation Description Performs wake relaxation on the WAKENET VORNET macroelements by an iterative technique Format and Example 1 2 3 4 5 RELAXW SETID MAXIT CONVERG OMEGA NPLOT FORM FILENM CONT Field Contents SETID Identification Number Integer gt 0 See Remark 1 MAXIT Maximum number of iterations Integer gt 0 Default 5 CONVERG Convergent criteria Real gt 0 0 Default 0 001 OMEGA Relaxation factor 1 0 gt Real 0 0 Default 0 5 NPLOT Incremental step at which the plot file for the wake shape is written on the external file FILENM Integer gt 0 NPLOT lt MAXIT FORM FORM TECPLOT for generating a TECPLOT file FORM for generating a PATRAN neutral file FORM IDEAS for generating an I DEAS universal file FORM FEMAP for generating a FEMAP neutral file FORM ANSYS for generating an ANSYS supported neutral file FORM NASTRAN for generating a NASTRAN bulk data deck FILENM The name of the data file in which the data for plotting the aerodynamic model with relaxed wake surface is stored This file name is always in the upper case In case the input file name is given the lower case the program converts it to the upper case Character
180. ROW may be derived from IS by L INT IS 65536 1 IROW IS 65536 L 1 Record 4 A J J IROW IROW L NC ND 1 5 16 9 For NTYPE 1 NC 1 ND 1 and A is a real single precision array NTYPE 2 NC 1 ND 2 and A is a real double precision array NTYPE 3 NC 2 ND 1 and A is a complex single precision array NTYPE 4 NC 2 ND 2 and A is a complex double precision array Records 3 and 4 are repeated for NW words EXECUTIVE CONTROL SECTION 3 23 ASSIGN MATRIX Records 2 3 and 4 are repeated for each column Record 2 with the last column number plus 1 and at least one dummy value in Records 3 and 4 must also be added at the bottom of the file Thus the total numbers of Record 2 in the file must be NCOL 1 An example is shown as follows 5 102 2 2MGH 1P 5E16 9 0 57 96611 6 855846336 03 96617 1 162878605E 02 96619 2 181833573E 03 96623 5 625212629E 02 96629 4 825029982 02 96635 6 989890183E 03 96641 6 215569848E 02 96647 1 509172999E 01 96653 1 093032792E 01 96677 1 173323700E 01 96683 2 918305947E 02 96689 7 453748578E 02 96695 9 896419781E 02 96700 5 763368009E 02 96707 1 495288195E 04 96709 1 115356274E 03 2 0 5T 96611 1 847709670E 02 96617 1 297997974 03 96619 2 976067064 04 96709 2 228496429 03 3 0 5T 96611 5 003520334E 02 96617 6 703697305E 02 96619 2 439368145E 03 96709
181. Real part of element see TIN of DMI bulk data card Real B Ix J Imaginary part of element see TIN of DMI bulk data card Real Remarks 1 is referred by the DMI bulk data card with entry LARGE DMIL The size and type of the matrix is defined in the DMI bulk data card 2 matrix elements is shown as follows A LI A L2 A LN AQ AQ 2 AQ N 1 A M 2 gt lt A M N where M is the number of rows and N is the number of columns M and N are defined in the DMI bulk data card 4 80 BULK DATA DESCRIPTION DMIL 3 For symmetric matrix only the input of the upper triangular part including the diagonals is allowed i e I lt J 4 Only nonzero terms need to be entered Therefore I1 I2 etc are the row locations of the first nonzero element in the J column 5 Complex input must have both the real and imaginary parts entered if either part is nonzero i e the zero component must be inputted explicitly Example of a Complex Matrix 5 0 0 01 7 04 7 0i 0 0 0 01 0 0 0 01 6 0 6 01 4 04 4 01 QQQ 4 042 001 0 0 0 01 6 DMIL can be repeatedly specified for each column of the matrix For columns that are not referred to by the DMIL bulk data card null columns are assumed BULK DATA DESCRIPTION 4 81 DMIS DMIS Matrix Element Value Definition by 8 Column Fields Description Defines the values of the matrix elements by 8 column fields DMIS is
182. S Compatible Output The I DEAS compatible output is saved in the universal file format Data sets 781 and 780 are used to output the aerodynamic grid points and panels respectively Data set 56 is used to output the pressure and is output four times for displaying the real imaginary magnitude and phase angle of the pressure The first five ID lines of each data set 56 list the following information Line 1 Line 2 Line 3 Line 4 Line 5 Pressure component of the current data set PLTCP Bulk Data Card identification number The number of aerodynamic grid points in the model The number of aerodynamic panels in the model The pressure component of the current data set i e real imaginary magnitude or phase angle repeated from Line but more descriptive A sample of the I DEAS compatible output is shown in the following figure ex 781 SIS 1 0 1 0 1 0 EX 780 201 0 0 11 000000000000000D 02 0 0000000000000000D 00 0 0000000000000000D 00 202 0 0 11 000000000000000D 02 0 0000000000000000D 00 0 0000000000000000D 00 203 0 0 11 000000000000000D 02 0 0000000000000000D 00 0 0000000000000000D 00 204 0 0 11 000000000000000D 02 0 0000000000000000D 00 0 0000000000000000D 00 Aerodynamic Grid Points 201 94 1 100000 1 1 1 4 202 207 206 201 202 94 1 100000 1 1 1 4 203 208 207 202 203 94 1 100000 1 1 1 4 204 209 208 203 204 94 1 100000 1 1 1 4 Quadrilateral Elements PLoT FILES 7
183. T to NONE Units of length used in the structural finite element model as well as all length dimensions involved in the aerodynamic model Must be one of IN FT MM CM KM or NONE Character Default NONE See Remark 3 Reference chord length Units must be in FMLUNIT Real gt 0 Default 1 0 See Remark 4 Reference span length Units must be in FMLUNIT Real 2 0 Default 1 0 See Remark 4 Reference area Units must be in FMLUNIT 2 Real gt 0 Default 1 0 Note that the reference area should account for the area on both the right hand and the left sides of the configuration even if only a right hand side configuration is modeled i e XZSYM YES See Remark 4 Location of aerodynamic moment center for computing aerodynamic force and moment coefficients due to rigid body motion Real See Remark 5 4 22 BULK DATA DESCRIPTION AEROZ Remarks 2 This card must exist Only one AEROZ is allowed ZONAIR assumes that the flow is in the positive x direction in the basic coordinate system and that the aerodynamic model is on the right hand side of the x z plane i e positive y direction However for the spline module that requires the perfect overlapping between the aerodynamic model and the structural the structural model may be oriented in an arbitrary coordinate system In this case for the displacements and loads spline between the aero
184. TAL COUNT EIGENVALUE ANALYSIS SORTED ote 2 Xu 3 3 10101 3 10201 3 10301 3 10401 1010 1010 1001 1000 1002 1000 1003 1000 1004 1000 1005 1000 1006 1000 1007 1000 1008 1000 1009 1000 20 10101 10102 10103 10104 10201 10202 10203 10204 10301 10302 10303 10304 10401 10402 10403 10404 20000 1100 1 07 COUPMASS1 WTMASS 00259 1010 1100 1000 1100 10 126 10 126 10 126 10 126 10 123456 BLOCK SIZE USED a 4 THRU THRU THRU THRU 10102 10101 10102 10103 10201 10202 10203 10301 10302 10303 0 0 33 333 66 667 100 000 16 667 44 444 72 222 100 000 23 333 55 555 77 778 100 000 50 000 66 667 83 333 100 000 33 333 100 T 5 10101 10201 10301 10401 20000 NUMBER OF DECOMPOSITIONS NUMBER OF ROOTS FOUND NUMBER OF SOLVES REQUIRED 43 B 1010 1020 1030 1040 2000 1010 1010 1010 1020 1020 1020 1030 1030 1030 30 0 30 0 30 0 30 0 5353 5343 53 3 53 3 76 6 76 6 76 6 76 6 100 100 100 100 0 0 3 1 1100 THRU THRU THRU THRU SUMMARY D UL 5 4 4 4 4 0 2 3 4 2 3 4 2 3 4 00 00 00 00 33 33 33 33 67 67 67 67 000 000 000 000 04 ECK ECH K DATA 10101 10202 10203 10204 10302 10303 10304 10402 10403 10404 Ooooooooooooooooo Ooooooooooooooooo 1 04 10104 10204 10304 10404 10201 10202 10203 10301 10302 10303 10401 10402 10403 ECHO 05
185. THE ZONA LICENSE SERVER ZLS The ZONA License Server ZLS has been developed by ZONA Technology Inc ZONA to act as the security license server for ZONA s software products The ZLS operates with the Sentinel Protection Installer SuperPro hardware key that is developed by SafeNet http www safenet inc com The ZLS is described in detail in the ZLS User s Manual that is installed with the ZLS software ZONAIR 4 1 is a network ready version of ZONAIR that requires the ZLS to be installed During each ZONAIR execution a token is checked out from the server and checked back in to the server when the job terminates There are two types of ZONAIR installations that can be made 1 Node Locked The 71 5 is installed on the same machine where ZONAIR is installed If ZONAIR runs on a stand alone machine both ZONAIR and ZLS must be installed as node locked 2 Floating License ZONAIR and the ZLS are installed on separate machines connected on a network Note that if desired tokens managed by the node locked ZLS can also be checked out by ZONAIR jobs executed from any machines that can access the node locked machine running the ZLS 2 7 1 THE JAVA ENVIRONMENT Java JRE 1 3 1 or later versions is required to run both the ZLS and ZONAIR For Windows UNIX or Linux platforms download and installation instructions can be found from the Internet ZONA can provide this download installation information if requested
186. URFZ and AESLINK is degrees The unit of PZTMODE JETFRC and GRIDFRC is defined by the users and is marked as N A in the output e User Defined Trim Variables The character string specified in the LABEL entry that does not match any of the program assigned and control surface type of the trim variables are classified as user defined trim variable For the user defined trim variables the entries SYM DCD DCY DCL DCR DCM and DCN in the TRIMVAR bulk data card must be specified Note The unit of the user defined trim variables is defined by the user and is marked as N A in the output 3 LOWER and UPPER are the so called side constraints for solving the over determined trim system Thus the solution of the free trim variables defined as FREE in the VALi entry of the TRIM bulk data card must be within LOWER and UPPER 4 If TRIMLNK 0 then the trim variable is not linked with other trim variable For description of trim variable linking please see TRIMLNK bulk data card 5 DMI provides a feature that allows the user to replace the program computed dC d trim variable of the rigid aircraft by those computed by other aerodynamic methods or wind tunnel measurement If DMI is a character string that is the name of a matrix the matrix either imported by the DMI bulk data card or the ASSIGN MATRIX Executive Control Command must have one column and J set rows where J set is the number of aerodynamic pa
187. X1 X2 X3 Not used PA PB Flags for infinite vortex line at points GA and GB respectively Integer gt 0 Default 0 See Remark 3 If PA or PB Z 0 PA represents a surface grid ID at which this infinite vortex line originates 1 e the grid point at the leading edge of the wing tip See the figure below Remarks 1 CBAR is to generate a sheet of constant doublet by sweeping the segment defined by the two grid points along the x direction to infinity See Figure Below It is usually placed at the trailing edge of the thick wing model and at the rear edge of the body 2 y GB f heet GA g constant doublet shee x i oo 2 For a truncated end body the CBAR s must be attached to the trailing edge of all panels at the end of the body BULK DATA DESCRIPTION 4 53 CBAR CBAR CH To model a thick wing type body two grid points that have the same X Y and Z locations must be specified at the trailing edge of the body Two CBAR s are attached to the upper and lower side of the trailing edge In this way the potential jump of the wake effect can be represented by the potential difference between these two wake sheets CBAR 3 For PA 0 or PB Z 0 program will automatically generate a line vortex starting from grid point GA or GB and extending to infinity GB GA line vortex for PB 0 line vortex for PA z 0 4 54 BULK DATA DESCRIPTION CORDIC
188. a TRIMFNC bulk data card whose value is represented by the symbol Fy shown in the above equation Integer gt 0 Co Real coefficients shown in the above equation Real Default 1 0 SYMBOL Character string either or see the symbol shown in the above equation Character F Identification number of a TRIMFNC bulk data card whose value is represented by the symbol F shown in the above equation If F is zero the value is assumed to be zero Integer 2 0 Real coefficients shown in the above equation Real Default 1 0 Real coefficients shown in the above equation Real Default 1 0 4 182 DATA DESCRIPTION TRIMADD Remarks IDFNC is referred to by the TRIMOBJ x y and z components respectively of a vector from the aerodynamic moment center REFX REFY and REFZ in the AEROZ bulk data card to the center of gravity C G of the configuration Thus the center of gravity is computed by 1 And TRIMCON bulk data cards to define the objective function and constraint functions for over determined trim systems IDFNC can also be referred to by the TRIM bulk data card through the SET1 bulk data card to print out the values of the trim functions TRIMADD can be used to construct a trim function by a complex expression that cannot be defined by a single TRIMFNC bulk data card The following example shows how to construct the Von Mises stress formula by the
189. a direct matrix input to replace the pressure coefficient computed by ZONAIR DATA DESCRIPTION 4 9 Generates Aerodynamic Influence Coefficient AIC matrix at a given MACH y AIO Required Mach Number OMITCFD Defines the surface mesh index of a structured CFD mesh Optional WTI1AJJ Corrects the AIC matrix by a force moment correction matrix Optional ifies a set of component forces and moments for generalizing thi i WTIFRC Spec es a set of component forces d moments for gene g the Op onal AIC weighting matrix WT2AJJ Corrects the AIC matrix by a downwash weighting matrix Optional Figure 4 4 depicts the interrelationships of the bulk data card for aerodynamic analysis Case Control Section AEROGEN Y PLTCP AEROGEN MACH Post processing of Identification Generate AIC aerodynamic analysis Number K matrix INPCFD INPCFDI CPSPLN Import steady mean Import steady mean Maps the wind tunnel flow solution flow solution measured pressure coefficients structured mesh unstructured mesh onto ZONAIR panels The appearance of a MACH bulk data card in the Bulk Data Section triggers the computation of the AIC matrix even if this MACH bulk data card is not referred to by any other bulk data card Note that the AIC matrix is only dependent on the Mach number and the aerodynamic panel model it can be reuse
190. ace due to a typo in the ACOORD bulk data card In this case the store would be located somewhere other than its intended position This error in the aerodynamic configuration can quickly be detected by viewing the aerodynamic model Figure 7 1 Plot of the Aerodynamic Model The PLTAERO output plot file contains the aerodynamic panel corner grid points along with the aerodynamic panel connectivity information The data for this output file is generated based on the GRID CQUAD4 CTRIA3 CBAR etc specified in the bulk data section of the input deck 7 2 PLorFiLES PATRAN Compatible Output The PATRAN compatible output is saved in neutral file format A sample of the NASTRAN compatible output is shown in the following figure and is described below 25 0 0 1 0 0 0 0 0 ZONAIR AERODYNAMIC MODEL 26 0 0 1 91 65 1 1 0 08 22 200015 31 31 2 5 1 201 0 2 0 0 0 0 0 0 100000000E 03 0 000000000E 00 0 000000000 00 oG 6 0 0000000 1 202 0 2 0 0 0 0 0 0 100000000E 03 0 000000000 00 0 000000000E 00 oG 6 0 0000000 Tae Aerodynamic Grid Points 2 201 2 0 0 0 0 4 0 1 0 0 000000000E 00 0 000000000E 00 0 000000000 00 202 207 206 201 2 202 4 2 0 0 0 0 0 4 0 1 0 0 000000000E 00 0 000000000E 00 0 000000000 00 203 208 207 202 2 203 4 2 0 0 0 0 0 4 0 1 0 0 000000000 00 0 000000000E 00 0 000000000 00 204 209 208 203 nm Quadrilateral Elements 31 10101 0 1 0 0 0 0 0 0 300000000E 02 0 000000000E 00 0 000000000E 00 31 1
191. ach numbers and at 9596 of the wing box chord for supersonic Mach numbers The solid and the dashed lines in the wake region of the thin wing in Figure 5 16 represent the vortex lines generated by each strip of the CAERO7 macroelement The solid lines represent the so called strong vortex line whereas the dashed lines represent the weak vortex line GUIDELINES FOR AERODYNAMIC MODELING 5 9 Spanwise Chordwise Divisions Bp Wing Box Note Spanwise Divisions must be Parallel with Free Stream Direction I I i I l I 1 Vortex Lines I I I I I I I 1 V V V Figure 5 16 CAERO7 Wing Macroelement for Thin Wing Modeling These vortex lines are generated due to the discontinuity between vortex singularities for two adjacent strips Each strip sheds two strong vortex lines from its side edges that start at the trailing edge and shed downstream Figure 5 17 a However at edges shared by two adjacent strips the strength of the two vortex lines partially cancels each other forming a weak vortex line Figure 5 17 b No input is required by the user to model these vortex lines since their effects are already included as part of the vortex singularity on the wing boxes However due to the singular behavior of the vortex line several restrictions must be adhered to in modeling the thin wing by CAERO7 WOW OM Figure 5 17 Vortex Lines Shed from CAERO7 Chordwise Strips Fi
192. achine requirements It is recommended that the filename be enclosed by single right hand quotation marks Remarks 1 INCLUDE statement may be nested that is an INCLUDE statement may appear inside the external file to refer to another file 2 The INCLUDE statement does not allow continuations The total length of the statement must be 72 characters or less BULK DATA DESCRIPTION 4 99 INPCFD INPCFD Description Replaces ZONAIR Solution by CFD Solution Imports the steady mean flow solution by interpolating the Computational Fluid Dynamics CFD Solution computed at a structured mesh to the ZONAIR surfaces panel model Format and Example 1 2 3 4 5 6 7 8 9 10 INPCFD IDCFD TRANSF OMITCFD FORMCFD CFDMESH CFDOUT INPCFD Field IDCFD TRANSF OMITCFD FORMCFD 20 1 P3D CFD GRID CFD P3D Contents If IDCFD is a positive integer it refers to the identification number of an AEROGEN bulk data card The pressure coefficients on the rigid aircraft at the flight condition defined by the AEROGEN bulk data card with ID IDCFD computed by the program are replaced by the CFD solution Integer If IDCFD is a negative integer it is referred to by a TRIMINP bulk data card Integer See Remark 1 Identification number of a CORD2R bulk data card defining a coordinate system in which the CFD mesh is located Note that TRANSF can be a negative integer This negative sign implies that the CFD mesh is loca
193. acter Default TECPLOT See Remark 4 BULK DATA DESCRIPTION 4 143 PLTMODE FILENM The name of the data file in which the data for plotting the interpolated structural mode is stored This file name is always in the upper case In case the input file name is given in the lower case the program converts it to the upper case If the first character starts with a dollar sign the rest of the characters must be integers This integer is the identification number of an EXTFILE bulk data card where the filename is specified This feature allows for filenames up to 72 characters to be input Character AERONM The name of a data file in which the aerodynamic model is stored in a PATRAN neutral file ONLY USED IF FORM PATRAN Character Default See Remark 5 Remarks l SETID is not referred to by other bulk data cards The existence of each PLTMODE the bulk data input triggers the generation of a data file for the purpose of plotting the interpolated structural mode on the aerodynamic model SETID is used for error message output only Note that PLTMODE bulk data card is activated only if the Executive Control Command SOLUTION 1 is specified PLTMODE generates a data file that contains one interpolated structural mode with index MODE This structural mode is defined in the ASSIGN FEM executive control statement with BOUNDARY SYM The interpolation of structur
194. aerodynamic boxes respectively Structural grid points are displayed as points through DATA Block 570 The ANSYS output is a FEMAP neutral file that can be read in by an ANSYS neutral file translator developed by PADT Inc For the use of IPS TPS and BEAM methods please see Modeling Guidelines of SPLINE described in Chapter 6 BULK DATA DESCRIPTION 4 69 CQUAD4 CQUAD4 Quadrilateral Aerodynamic Panel Description Defines a quadrilateral aerodynamic surface panel by four surface grid points Format and Example I 2 3 4 5 6 7 8 9 10 CQUADA EID PID G1 G2 G3 G4 CQUAD4 10 1 3 6 8 101 Field Contents EID Unique panel identification number Integer gt 0 See Remark 1 PID Identification number of a PSHELL bulk data card Integer gt 0 See Remark 2 Gl G2 Identification numbers of connected grid points GRID bulk data cards G must be the G3 G4 surface grid PS 0 in the GRID bulk data card Unique Integer gt 0 See Remark 3 Remarks 1 Among CQUADA CTRIA3 CAERO7 and BODY7 bulk data cards EID must be unique 2 The PSHELL bulk data card must exist 3 sequence of the four corner grid points defines the out normal vector of the panel See figure below 3 The user must ensure the out normal vector is toward outside the aerodynamic model Incorrect out normal vector will definitely lead to wrong results Note e The program subdivides
195. al GENM Generalized mass of the modes Real Example 38 23 0 032 Card Set 4 ID T Ri Ro Free Format ID Identification number of the structural grid point must exist in card set 2 Integer gt 0 To Translational modal displacement in x y and z directions Real R Ro Rotational modal displacement about x y and z directions Real Example 100 00 00 33 21 05 40 Repeat card set 4 NGRID times for the modal displacement at all grid points Go back to card set 3 Repeat this process NMODE times for all modes Comment cards may be used in a modal data file with FORM FREE format and must be initiated with a in the first column 3 16 EXECUTIVE CONTROL SECTION ASSIGN FEM An example for FORM FREE is shown as follows EXAMPLE CASE WITH FORM FREE 17 5 10101 0 0000 30 0000 0 0000 10102 33 3330 30 0000 0 0000 10103 66 6670 30 0000 0 0000 10104 100 0000 30 0000 0 0000 10201 16 6670 53 3330 0 0000 10202 44 4440 53 3330 0 0000 10203 72 2220 53 3330 0 0000 10204 100 0000 53 3330 0 0000 10301 33 3330 76 6670 0 0000 10302 55 5550 76 6670 0 0000 10303 77 7180 76 6670 0 0000 10304 100 0000 76 6670 0 0000 10401 50 0000 100 0000 0 0000 10402 66 6670 100 0000 0 0000 10403 83 3330 100 0000 0 0000 10404 100 0000 100 0000 0 0000 20000 33 3330 0 0000 0 0000 MODE 1 0 28983E 02 0 10000E 01 10101 0 00000E 00 0 00000E 00 0 24389E 00 0 10465 02 0 13886E 01 0
196. al modes from the structural grid points to the aerodynamic model is performed by the SPLINE module Graphical display of the interpolated mode is useful to detect any error in the spline input Since the structural mode is the eigenvector obtained by the structural analysis the magnitude of the mode may not be of the same order as the size of the aerodynamic model To circumvent this problem it is recommended to define the maximum displacement of the mode by MAXDISP x REFC The format of the data file is defined by the FORM entry The interpolated modal data are added to the x y and z values of the aerodynamic grids to create a deformed aerodynamic model Using the TECPLOT or PATRAN software depends on FORM TECPLOT or PATRAN the deformed aerodynamic model can be displayed graphically For I DEAS universal file output data sets 781 and 780 are used for displaying the aerodynamic grids and boxes respectively A data set 55 is used to output the six degree of freedom displacements at all aerodynamic grid For FEMAP neutral file format Data Blocks 403 and 404 are used for displaying the aerodynamic grids and boxes respectively Data Block 451 is used for displaying the deformed mode shape TOTAL Translation X axis translation T1 Y axis translation T2 and Z axis translation T3 The interpolated mode shape can either be statically deformed or animated The ANSYS output is a FEMAP neutral file that can be read in by an ANSYS neutral
197. alysis Optional TRIMVAR Defines a trim variable for the static aeroelastic trim Required if a TRIM bulk analysis data card is active The interrelationship between the bulk data cards for static aeroelastic trim analysis is depicted in Figure 4 7 In addition to the above listed bulk data cards the PLTTRIM bulk data card specified in Section 4 2 6 can be used to generate the plot files of the deformed aerodynamic model and steady pressure distributions In addition PLTTRIM can be used to generate a file that contains the flight loads in terms of NASTRAN FORCE and MOMENT bulk data cards at the structural finite element grid points The user can insert this file back to the finite element model to perform a static analysis for detailed stress calculations BULK DATA DESCRIPTION 4 13 Executive Control Command PLTTRIM Case Control Section ASSIGN MATRIX FILENM Post processing ofthe Subcase n MNAME trim results TRIM K and or ASSIGN MATRIX FILENM MNAME AMGH Y SMGH and or AMGH for distributed inertial loads calculation TRIM AEROGEN Required only for over determined trim system t ui Bulk data card with Fhght Condition identification number K Y TRIMOBJ TRIMCON DMI TRIMVAR Defines an objective Defines a set
198. an link a set of finite element grid points in 3 D space to either a wing like or body like component The ATTACH bulk data card handles the special case in which a component is absent in the finite element model but is present in the ZONAIR model A typical example of such a special case is an underwing store that is represented by a concentrated mass at a single finite element grid point but is completely modeled in the ZONAIR model Experience has shown that most of the errors in performing flexible loads analysis are introduced in the spline procedure The following modeling guidelines present several situations in which inaccurate spline results are easily introduced due to incorrect input set up MODELING GUIDELINES OF SPLINE FOR FLEXIBLELOADS 6 1 6 1 ILL CONDITIONED SPLINE MATRIX DUE TO COINCIDENT FINITE ELEMENT GRID POINT LOCATIONS The selection of the finite element grid points that are to be linked to an aerodynamic component is completely at the user s discretion These grid points are defined by SET1 or SET2 bulk data cards Should two of the selected finite element grid points be located within a small tolerance of one another tolerance set by EPS defined in the SPLINE1 and SPLINE3 bulk data cards the resultant spline matrix is either singular or ill conditioned This input error is automatically detected by the ZONAIR spline module However certain scenarios exist in which this kind of input error may not be detected by the spl
199. and with BOUNDARY ANTI For the asymmetric trim system involving both longitudinal and lateral trim degrees of freedom both free vibration solutions must be imported However if the configuration is asymmetric about the x z plane XZSYM NO in the AEROZ bulk data card only one free vibration solution with BOUNDARY ASYM is required In addition to the free vibration solutions for computing the distributed inertial loads the static aeroelastic trim analysis also requires a matrix called SMGH for the symmetric trim system a matrix called AMGH for the anti symmetric trim system and both for the asymmetric trim system that are imported by the ASSIGN Executive Control Command The distributed inertial loads exist only if the structural finite element model contains rigid body degrees of freedom a non zero integer specified by the SUPORT 4 14 BULK DATA DESCRIPTION entry of the ASSIGN FEM Executive Control Command The equation for computing the inertial loads of a symmetric trim system reads Uu where UJ MGG PHG t j n PHG t MGG X MGG PHG ii SMGH i is the distributed inertial loads is the mass matrix of the structural finite element model defined in the G set d o f is the modal matrix of the free vibration solution that is imported by the ASSIGN FEM Executive Control Command represents the accelerations of the tri
200. andle data conversion For little endian usage the CFD files were generated in the same type of computer system as the one where ZONAIR is running For big endian usage the ZONAIR is running on a little endian system such as PC Windows but the CFD files were generated in a big endian computer system For instance for a unformatted and double precision CFD solution with IBLANK array and being normalized for p 21 0 and P 21 0 FORMCFD IUDP3DB2 if big endian is true and FORMCID IUDP3D2 if Little endian is true Character default P3D BULK DATA DESCRIPTION 4 101 INPCFD CFDMESH Character string up to 16 characters to specify the file name that contains the CFD mesh If the first character starts with a dollar sign the rest of the characters must be integers This integer is the identification number of an EXTFILE bulk data card where the filename is specified This feature allows for filenames up to 72 characters to be input Character See Remark 5 CFDOUT Character string up to 16 characters to specify the file name that contains the CFD solution If the first character starts with a dollar sign the rest of the characters must be integers This integer is the identification number of an EXTFILE bulk data card where the filename is specified This feature allows for filenames up to 72 characters to be input Character See Remark 6 Remarks l The INPCFD bulk data ca
201. anels and they are the causes for numerical singularities in the supersonic aerodynamic influence coefficient computation Domain of Influence Superinclined Panels Domain of Influence b Figure 5 20 Superinclined Panels on Engine Inlet b on Thick Body To circumvent this numerical singularity problem that is associated with super inclined boxes in supersonic flow we introduce a special treatment for the aerodynamic influence coefficient computation in ZONAIR This engineering treatment adopts the corresponding oblique shock angle for a cone based on the Exact Euler Conical Flow Solutions to compute the Mach wave angle The local cone angle for each superinclined box is measured by the angle between the freestream and the slope of the panel The corresponding oblique shock angle is used as a modified Mach wave angle to position a Mach Wave slightly ahead of the super inclined panels It is this modified Mach angle that determines the region of influence of the super inclined panels 5 12 GUIDELINES FOR AERODYNAMIC MODELING 5 8 MODELING OF THE REAL FLOW USING THE POTENTIAL FLOW THEORY Unlike the Computational Fluid Dynamics CFD methodology that simulates the flow the panel method solves the potential flow equation that can only be used to model the flow This is to say that in order to establish a good panel model that can capture most of the physics of the flow the user must understand t
202. are treated as the rigid loads to compute the flexible loads due to the static aeroelastic effects by the TRIM and FLEXLD bulk data cards 2 Because the wind tunnel model may be oriented in an arbitrary fashion with respect to the aerodynamic model it is required to transform the wind tunnel model so that the wind tunnel model and the ZONAIR BULK DATA DESCRIPTION 4 67 CPSPLN aerodynamic model overlap with each other This can be achieved by introducing a CORD2R bulk data card with identification number IDCOR that defines a coordinate system where the wind tunnel model is located In the following figure the X Y Z system is the local coordinates defined by CORD2R bulk data card whereas X Y Z is the aerodynamic coordinates of the ZONAIR aerodynamic model 2 y Wind Tunnel Model Jennie ZONAIR pee Aerodynamic Aerodynamic SELL Model Mosel s d x Points A B C x Of CORD2R Definition In the example the nose of the fuselage of the wind tunnel model is located at x z 0 and y 100 with respect to the ZONAIR aerodynamic model whereas that of the ZONAIR aerodynamic model at x y z 0 To transform the wind tunnel model it is required to specify a CORD2R bulk data card such as ICORD2R 50 0 0 100 0 0 0 0 0 100 0 1 0 C C 0 0 101 0 1 0 In addition because the above figure shows that the wind tunnel model is located in the negative axis the entry IDCO
203. at FORM FORMAT Record 1 NCOL NROW NF NTYPE NAME 418 A8 NCOL Number of columns NROW Number of rows NF Form of matrix NF 2 General rectangular matrix NF 6 Symmetric matrix Only the upper triangular part including diagonals is input NTYPE Type of matrix NTYPE 1 Real single precision NTYPE 2 Real double precision NTYPE 3 Complex single precision NTYPE 4 Complex double precision NAME Character string up to 8 characters If no MNAME c is specified these characters are used as the name of the matrix Record 2 ICOL ROW NW 318 ICOL Column Number IROW Row position of the first nonzero term NW Number of words in the column For a complex matrix there are two words for each element of the matrix Record3 AJ J IROW IROW NW NC 1 5 16 9 for FORM FORMAT 3D23 16 for FORM FORMAT23 9 For NTYPE 1 NC 1 and A is a real single precision array 2 NC 1 and A is a real double precision array 3 NC 2 and A is a complex single precision array NTYPE 4 NC 2 and A is a complex double precision array EXECUTIVE CONTROL SECTION 3 21 ASSIGN MATRIX Records 2 and 3 are repeated for each column Record 2 with the last column number plus 1 and at least one dummy value in Record 3 must also be added at the bottom of the file Thus there are a total of NCOL 1 numbers of Records 2 and 3 in the file An example is shown as f
204. ate system identification numbers ID on all ACOORD bulk data cards must be unique 2 If ACOORD is referenced by a BODY7 bulk data card the X axis of the coordinate system defines the centerline of the body 3 coordinate locations are with reference to the basic coordinate system ACOORD defines rectangular coordinate system whose X axis must be parallel to the X axis of the basic coordinate system 4 Since most underwing stores have a small inclination angle to the free stream DELTA can be used to provide a simpler means for defining this inclination Definition of Angle DELTA Definition of Angle THETA 4 18 BULK DATA DESCRIPTION AEFACT AEFACT Description Used to specify lists of real numbers Format and Example List of Real Numbers Embedded blank fields are forbidden d 2 3 4 5 6 7 8 9 10 AEFACT SID D1 D2 D3 D4 D5 D6 D7 CONT CONT D8 etc AEFACT 97 lt 3 7 1 0 Field Contents SID Set identification number Unique Integer gt 0 Di Number Real Remarks BULK DATA DESCRIPTION 4 19 AEROGEN AEROGEN Description Format and Example condition 1 2 5 Computes Aerodynamic Results Computes aerodynamic pressure coefficients forces and moments at a specified flight 6 7 8 9 10 AEROGEN IDAERO IDMACH ALPHA BETA PRATE
205. ation numbers If used for spline it SETI contains a list of identification numbers of structural finite Optional element grid points 4 16 BULK DATA DESCRIPTION 4 3 BULK DATA DESCRIPTIONS This section contains a complete description of each ZONAIR bulk data card BULK DATA DESCRIPTION 4 17 ACOORD ACOORD Aerodynamic Coordinate System Description Defines a local coordinate system for an aerodynamic component referenced by the BODY7 or CAERO7 bulk data cards Format and Example 2 3 4 5 6 7 8 9 10 ACCORD ID XORIGN YORIGN ZORIGN DELTA THETA ACOORD 10 250 0 52 5 15 0 0 0 0 0 Field Contents ID Coordinate system identification number Integer gt 0 XORIGN A YORIGN X Y and Z location of the component origin Real ZORIGN DELTA Pitch angle in degrees measured from the X Z axes of the basic coordinate system to the X Z axes of the component coordinate system positive in direction shown see Remark 4 figure This parameter will not physically rotate the model Its effects are introduced in the boundary condition Therefore DELTA must be a small value Real See Remark 4 THETA Roll angle in degrees measured from the Y Z axes of the basic coordinate system to the Z axes of the component coordinate system positive in direction shown see Remark 4 figure Unlike DELTA THETA will physically rotate the model Real Remarks 1 Coordin
206. ber free stream speed of sound p free stream density free stream pressure U free stream velocity T stream temperature universal gas constant p local pressure u local u velocity component v ocal v velocity component w local w velocity component T local temperature s entropy y ratio of specific heats y 14 4 108 BULK DATA DESCRIPTION INPCFDI A FIELDVIEW subscript fv 1 Non dimensional Pressure A 1 Polis 2 Non dimensional U Velocity ug uf u A 2 Uso 3 Non dimensional V Velocity v vA ave A 3 Us 4 Non dimensional W Velocity ws Why Ws A 4 0 5 Non dimensional Temperature E A 5 B INPCFDI subscript inp 8 variables Note ZONAIR requires that the velocity components be normalized by the speed of sound instead of the free stream velocity Therefore the velocity components from FieldView which are normalized by the free stream velocity U are multiplied by free stream Mach number to obtain velocity components that are normalized by the speed of sound 1 U Velocity Uinp inp u fy Mos B 1 2 V Velocity Vinp Vinp 2 3 W Velocity Winp Winp 3 4 Pressure Coefficient C D Cp 1 2 gt ool eS 2 p substituting from A 1 p p p U2 2 D fv Pees p Poo Cp inp 2pfy
207. between two SUBCASE Case Control Commands 2 The integer n is the identification number of the THERMAL bulk data card Integer gt 0 This THERMAL bulk data card must exist in the Bulk Data Section 3 THERMAL and n must be separated by an equal sign 3 42 CASE CONTROL SECTION TITLE TITLE Title of the Job Description Provides the title of the job by a character string up to 72 characters in length Format TITLE A Example TITLE ZONAIR Analysis of a Demo Case Remarks 1 Only one TITLE Case Control Command is allowed in the entire Case Control Section TITLE must appear before the SUBCASE Case Control Command 2 A represents a character string up to 72 characters in length to provide the title of the job 3 Ifno TITLE exists in a subcase section then the character string A is blank CASE CONTROL SECTION 3 43 TRIM TRIM Invokes the Static Aeroelastic Trim Analysis Discipline Description Invokes the static aeroelastic trim analysis discipline by referring to an identification number of the TRIM bulk data card If SOL 1 is specified in the Executive Control Section both trim results on the rigid and flexible configurations are computed Format TRIM n Example TRIM 103 Remarks l The TRIM Case Control Command must appear within a subcase section i e between two SUBCASE Case Control Commands The integer n is the identification numbe
208. board of the Wake Figure 5 14 RBE2 for Wake Modeling Behind the Wing Body Junction One could satisfy the closure condition by adding a infinite line vortex element CROD along this free edge However this line vortex is physically unrealistic because flow can not roll up at the wing body junction The correct modeling to satisfy the closure condition is to use the RBE2 bulk data card that automatically generates a set of CBAR elements along those body grid points behind the trailing edge of the wing body junction These CBAR elements serve two purposes 1 to fill up the gap so that the closure condition is satisfied 2 to impose the potential jump condition due to wake at those body grid points so that the potential jump is continuous from the wake to those body grid points For detailed description please refer to the description of the RBE2 bulk data card 5 8 GUIDELINES FOR AERODYNAMIC MODELING 5 6 THE THIN WING MODELING It is well known that the aerodynamic influence coefficient matrix may become ill conditioned if two surface panels are very close to each other due to the singularity behavior of the kernel integral In fact the matrix is singular if two surface panels coincide with each other The ill conditioned matrix may occur on a wing of very thin thickness if the upper and lower surfaces of the wing are modeled by the surface panels To circumvent this problem a thin wing modeling technique using the CAERO7 bulk data card i
209. ces For trim variables PRATE QRATE and the unit is in 1 0 pb 2V 1 0 qc 2V and 1 0 rb 2V respectively INPCFD1 and INPCFD2 must be negative to refer to an INPCFD INPCFDI INPDMI or CPSPLN bulk data card that has a negative identification number BULK DATA DESCRIPTION 4 191 TRIMLNK TRIMLNK Trim Variable Linking Description Defines a set of coefficient and trim variable identification number pairs for trim variable linking Format and Example 1 2 3 4 5 6 7 8 9 10 TRIMLNK IDLINK COEFF IDVAR COEFF IDVAR COEFF 3 IDVAR CONT Field Contents IDLINK Unique identification number Integer gt 0 See Remark 1 SYM Character string to define the type of aerodynamic stability derivatives that are generated by the trim variable linking Character See Remark 2 SYM SYM for longitudinal stability derivatives SYM ANTI for lateral stability derivatives SYM ASYM for both longitudinal and lateral stability derivatives COEFF Coefficient to define the linear relationship between the dependent and independent trim variables Real See Remark 3 IDVAR Identification number of a TRIMVAR bulk data card to define a dependent trim variable Integer gt 0 See Remark 3 Remarks 1 IDLINK is referred to by the TIMLNK entry the TRIMVAR bulk data card The trim variable defined in the TRIMVAR bulk data card that refers to IDLINK is called independen
210. ch ACP en is computed or measured Note that after WT2 is computed the corrected AIC matrix defined as AJJ where AJJ AH WT2 is stored on the run time database to compute the flexible loads of all modes The entries TYPE and LABEL jointly define the type of mode that is used to generate ACp For instance if ACp is measured on a rigid aerodynamic wind tunnel model at an angle of attack TYPE RIGID and LABEL PITCH are recommended The entries Al INPCFD1 A2 and INPCFD2 jointly define the given pressure coefficients ACp as ACP gin Al Cp 42 Cp where Cp and Cp are imported through the entries INPCFD1 and INPCFD2 respectively For instance if Cp are the pressure coefficients at angles of attack a 1 and 0 respectively Al should be 180 n and A2 should be 180 so that ACP given a 1 Cp oJ Thus the resulting ACp NE is the derivative of the pressure coefficient with respect to a pitch mode with a unit pitch angle 4 222 BULK DATA DESCRIPTION Chapter 5 GUIDELINES FOR AERODYNAMIC MODELING This section presents some important aspects of ZONAIR aerodynamic modeling and is intended to provide information that has not been covered in the bulk data card descriptions ZONAIR has been developed with many checks to detect any errors in the aerodynamic input However there are certain situations whereby incorrect modeling is not
211. ched to the wake sheet The RBE2 bulk data card is used to satisfy the potential jump condition at those grid points 4 156 DATA DESCRIPTION RBE2 GRIDU and GRIDL must be the grid points at the junction of the trailing edge of the thick wing component and the body In the figure show below GRIDU 51 and GRIDL 52 Because CBAR WAKENET elements must be also defined at the trailing edge of the thick wing component by the user GRIDU and GRIDL are also implicitly attached to those CBAR WAKENET elements This condition will be automatically identified by the program If there is no CBAR WAKENET associated with GRIDU and GRIDL fatal error occurs GRIDU IDTE For a symmetric aerodynamic model XZSYM YES in the AEROZ bulk data card only modeling half of the configuration is required even for a vertical tail whose mean plane is located on the X Z plane This 18 to say that because of the absence of the left hand side surface of the vertical tail surface there 18 only one grid point at the trailing edge of the vertical tail s right hand side surface if it is modeled as a trick wing component and the fuselage junction In this case GRIDL 0 is required For CBAR YES the program will internally generate two sets of CBAR elements between these body GRID points starting from the GRID point at the root of the thick wing trailing edge One set of CBAR are attached to the body panels which are on the up
212. cing Step Infinite velocity Stream line Attached flow Panel on stream line a Real Flow b Incorrect Panel Model c Correct Panel Model Figure 5 22 Modeling of Flow Passing a Backward Facing Step Another example showing how to use the wake surface to model separated flow on an aft body is illustrated in Figure 5 23 In the real flow the fluid does not stagnate at a point at the aft end of the body but rather GUIDELINES FOR AERODYNAMIC MODELING 5 13 separates into a trailing wake It is recommended that the aft body be truncated at the separation line and use the wake surface to model the streamline outside the separated flow Figure 5 23 c Although the exact separation line may not be known it is likely that the error incurred will be less than if the flow is forced to remain attached and stagnated Figure 5 23 b The closed aft end model usually yields a solution with a poor lift and may also wrongly influence nearby lifting surfaces The preferred modeled for the open trailing wake is shown in Figure 5 23 c The body itself is modeled by the surface panels but with a wake surface attached to the truncated end of the body at the presumed separation line This will assure that the flow departs the body smoothly along the specified wake surface Rear Flow Separated wake Wake Not recommended a Real Flow b Incorrect Panel Model c Recommended Model Figure 5 23 Modeling of Aft Body 5 9 CO
213. computation of the GENAIC module aerodynamic matrix generation is completed The matrices exist on the run time database include the generalized aerodynamic force matrices of the FEM mode and control surfaces 3 The resulting matrix is computed based on the following equation RESULT COEFFA MATRIXA SYMBOL MATRIXB For example SMHH TRNS 2 0 SPHI MGH 4 The matrix MATRIXA and MATRIXB if SYMBOL Zz blank must already exist on the run time database Note that if the matrix RESULT exists on the run time database it will be replaced by the resulting new matrix 4 30 BULK DATA DESCRIPTION ALTER 5 following are examples of the applications using the ALTER bulk data cards to add mass to the generalized mass matrix such as SMHH SMHH SPHI DELTAM SPHI where SMHH is the symmetric generalized mass matrix SPHI is the symmetric modal matrix Note that SMHH and SPHI are imported by the ASSIGN Executive Control Command DALTAM contains the mass the g set d o f that is to be added into the generalized mass matrix Note that DELTAM can be defined by the DMIG bulk data card The following three ALTER bulk data cards can be used to perform the above task ALTER FEM TMP TRNS SPHI DELTA ALTER FEM TMP TMP SPHI ALTER FEM SMHH SMHH TMP BULK DATA DESCRIPTION 4 31 ATTACH
214. d Contents IDINP Identification number that is referred to by the TRIMVAR bulk data card Integer gt 0 See Remark 1 1 A factor applied to the imported pressure coefficients by the entry INPCFDI Real See Remark 2 INPCFDI A negative integer referring to an INPCFD INPCFDI INPDMI or CPSPLN bulk data card that imports the first set of user supplied pressure coefficients Integer lt 0 See Remark 3 A2 Same as A1 except for INPCFD2 INPCFD2 Same as INPCFDI except for the second set of user supplied pressure coefficients Integer x 0 FORM Format of the output file FILENM FORM TECPLOT for generating the TECPLOT file FORM PATRAN for generating the PATRAN neutral results file FORM IDEAS for generating an I DEAS universal file FORM FEMAP for generating a FEMAP neutral file FORM ANSYS for generating an ANSYS supported neutral file FORM for generating a NASTRAN bulk data deck Character Default TECPLOT FILENM The name of the data file in which the data for plotting the imported pressure derivatives on the aerodynamic model is stored This file name is always in the upper case In case the input file name is given in the lower case the program converts it to the upper case If the first character of FILENM starts with a dollar sign the rest of the characters must be integers This integer is the identification number of an EXTFILE bulk data card w
215. d for different flight conditions different a D 9 r etc Because the computation of AIC matrix is time consuming a SAVE RESTART capability is implemented in ZONAIR through the MACH bulk data card The SAVE in the MACH bulk data card entry is used to specify whether to save the AIC matrix of the current run or the Figure 4 4 Bulk Data Interrelationship for Aerodynamic Analysis read from a previously saved AIC file 1 e the restart process In the following conditions the restart process becomes inapplicable and a new AIC matrix must be computed i e entry SAVE cannot be ACQUIRE e Any change in the aerodynamic panel modeling e Any change in the MACH bulk data card 4 10 BULK DATA DESCRIPTION 4 2 4 Aeroheating Analysis There is only one bulk data card called THERMAL required to perform the aeroheating analysis Name Description Remarks Required for aeroheating analysis Performs the aeroheating analysis at a specified flight THERMAL condition Figure 4 5 shows the interrelationship of the THERMAL bulk data card with other bulk data cards Case ControlSection THERMAL K THERMAL AEROGEN All other bulk data cards referred to by AEROGEN IDAERO required with identification number IDAERO with identification number K Output plot file for post processing of aeroheating analysis Figure
216. d into the problem gap panel gap panel Since the wake shed from the thin wing trailing edge creates potential jump across wake sheet any body grids located on the plane of the wake sheet will experience the same potential jump This is to say that the doublet distribution is continuous over the body surface except at these grid points In the following figures there are two grid points on the body located on the plane of the wake sheet Therefore the identification numbers of the grid listed in the SET1 bulk data card are 709 and 1001 For a coplanar wing tail configuration only the grid points between the trailing edge of the wing and the leading edge of the tail included are listed in the SET1 bulk data card For instance for the configuration shown below there are three grid points namely 1 12 14 are listed in the SET1 bulk data card for the wing wake For the tail wake the grid points listed the SET1 bulk data card are 101 104 BULK DATA DESCRIPTION 4 49 CAERO7 Noted that once RWAKE is activated the program will internally generate two sets of CBAR elements one set is attached to CQUAD4 CTRIA3 panels located on the upper side of the wake sheet and the other set on the lower side of the wake sheet In the following figures there are four CBAR elements two on the upper side and two on the lower side are generated by the program Two
217. d the G set modal matrix of the structural finite element model G set is defined as 6 x number of structural finite element grid points The equations to obtain these matrices are shown as follows SMGH MGG PHG 5 MGG PHG 3 44 CASE CONTROL SECTION TRIM where MGG is the mass matrix of the G set d o f PHG is the symmetric modal matrix of the G set d o f and PHG is the anti symmetric modal matrix of the G set d o f SMGH and AMGH are used to compute the so called inertial coupling matrices between the structural modes and the control surface modes The following example shows the MSC NASTRAN DMAP alter statements that generate these matrices by the NASTRAN OUTPUTA module Note or is required only if the structural finite element contains rigid body degrees of freedom i e the SUPORT entry in the ASSIGN Executive Control Command specifies a non zero integer ASSIGN OUTPUTA4 demol mgh UNIT 12 FORM FORMATTED SOL 103 COMPILE SEMODES SOUIN MSCSOU LIST NOREF 5 ALTER STRAIN ENGERGY MATGEN EQEXINS INTEXT 9 LUSETS GENERATE EXTERNAL SEQUENCE MATRIX MPYAD MGG PHG MGHINT MGHINT IS THE MGH IN INTERNAL SEQUENCE MPYAD INTEXT MGHINT MGH 1 TRANSFORM MGHINT TO EXTERNAL SEQUENCE OUTPUTA MGH 1 12 2 OUTPUT TO UNIT 12 IN demol mgh ENDALTER CEND Once the demol mgh is generated by NASTRAN it can be directly input into ZONA
218. de Generator Description Defines the load mode of a set of aerodynamic panels for computing component loads Format and Example Field Contents LID LOADMOD identification number Integer gt 0 See Remark 1 LABEL Type of loads defined by the load mode Character Must be one of the following XSHEAR Shear force along X axis of the coordinate system CP YSHEAR Shear force along Y axis of the coordinate system CP ZSHEAR Shear force along Z axis of the coordinate system CP Bending moment about X axis of the coordinate system CP YMOMENT Bending moment about Y axis of the coordinate system CP ZMOMENT Bending moment about Z axis of the coordinate system CP CP Identification number of a rectangular coordinate system CORD2R bulk data card Integer 2 0 See Remark 2 SETK Identification number of PANLSTI PANLST2 or PANLSTS3 bulk data card used to define the aerodynamic panel id s Integer gt 0 SETG Identification number of SET1 bulk data card used to define the structural grid points Integer gt 0 used only for flexible loads analysis See Remark 3 Remarks 1 The LOADMOD bulk data card can be used to compute the loads including aerodynamic loads and inertial loads of a component for instance the wing or an under wing store All component loads defined by the LOADMOD bulk data card exist in the Bulk Data Section will be automatically computed 2 If CP 0 the basic coordinate syste
219. dge of the thick wing and body junction Integer 5 0 See Remark 2 Absolute value of GRIDL is the identification number of a surface grid point that is at the lower trailing edge of the thick wing and body junction Integer Z 0 See Remark 3 Character string either YES or NO If CBAR YES a set of CBAR elements are automatically generated by the program along GRIDU GRIDL and GRID Character Default YES See Remark 4 Optional input IDTE is the identification number of a grid point that is located at the thick wing trailing edge and is connected with GRIDU by a CQUAD4 CTRIA3 element The normal vector of this CQUAD4 CTRIA3 element is used to separate those panels along GRIDi into upper and lower sets of panels However if IDTE 0 this normal vector could be automatically determined by the program Integer Default 0 Absolute value of GRID is the identification number of a surface grid point on the body that is attached to the wake sheet generated by the thick wing component Note that GRID can be a character string AUTO In this case all GRIDi are not required for input They could be automatically determined by the program Integer Z 0 or Character see Remark 5 1 For a thick wing and body combination the wake sheet generated by the thick wing component creates potential jump discontinuity of velocity potential across the wake sheet at those grid points on the body component that are atta
220. dinate system by reference to coordinates of three points The first point defines the origin The second point defines the direction of the z axis The third lies in the plane of the azimuthal origin The reference coordinate system must be independently defined Format and Example 1 2 3 4 5 6 7 8 9 10 CORD2S CID RID Al A2 A3 B1 B2 B3 CONT CONT Ci C2 C3 CORD2S 3 17 2 9 1 0 0 0 3 6 0 0 1 0 23 23 5 2 1 0 2 9 Field Contents CID Coordinate system identification number Integer gt 0 RID Reference to a coordinate system which is defined independently of new coordinate system Integer 0 or Blank Ai Bi Coordinates of three points in coordinate system defined by RID Real Remarks 1 A continuation entry must be present 2 The three points A1 A2 BI B2 C2 C3 must be unique and noncollinear 3 Coordinate system identification numbers on all CORDIR CORDIC CORDIS CORD2R CORD2C and CORD2S entries must all be unique 4 64 BULK DATA DESCRIPTION CORD2S An RID of zero references the basic coordinate system The location of a grid point P in the sketch in this coordinate system is given by R 0 where 0 and are measured in degrees The displacement coordinate directions at P are shown above by u ue Ug Points on the polar axis may not have their displacement directions defined in this coordinat
221. dule called ZSTREAM that adopts the inviscid surface velocities generated by ZONAIR as input to yield high quality streamline solutions Streamline Results of a CKEM at M 6 0 and 2 b 15 Blunt Cone at M 10 6 and a 5 c X 34 at M 6 anda 9 e the streamlines are obtained the aeroheating analysis can be performed along each streamline using a simple one dimensional boundary layer method INTRODUCTION 1 9 one dimensional hypersonic boundary layer method is developed based on the similarity solutions of compressible laminar turbulent boundary layer methodology of Eckert Boeing RhorMa and the White Christoph methods cem ZONAIR CFL3D Euler LATCH 5 ZONAIR SHABP e 6 E a x in Laminar Heat Transfer Rates Btu ft2 s on 15 Blunt Cone at M 10 6 a 5 2 66 lb ft T 89 971 R Tw 540 R Wake Relaxation Gun lanuched projectile with oblique wing at M 0 6 a 4 e Flat wake generated from wing cuts into body which creates singularities in computations e Wake relaxation generates curved wake surface that removes the problem Curved Wake by Wake Relaxation ZONAIR 079 CFL3D Pressure Coeficiont 1 10 INTRODUCTION 1 7 SPLINE MODULE The 3D Spline module establishes the displacement force transferal between the structural Finite Element Meth
222. dynamic and structural models the structural grid points will be transformed to the aerodynamic coordinate system according to ACSID It is possible that the structural model may be located on the left hand side 1 negative y axis of the coordinate system ACSID this situation the structural model can be flipped from the left to the right hand side by specifying FLIP YES For a symmetric model about the x z plane ZONAIR generates the symmetric and anti symmetric aerodynamic influence coefficient matrices simultaneously for all Mach numbers specified in the MACH bulk data card FMLUNIT is the length unit involved in the structural analysis The unit of length of the aerodynamic model must also be in FMLUNIT Thus the units of length of structural and aerodynamic models must be the same FMMUNIT formerly required as input is automatically set to be a consistent mass unit based on the input length unit For example if the length unit is meters the mass unit will end up kilogram if the length unit is inches the mass unit will end up slinch and so on In other words for any metric length unit input a N will automatically be applied for the mass unit and if English length unit is input a LBF will automatically be applied for the mass unit This always ensures that consistent units are used The non dimensional aerodynamic force and moment coefficients are defined as Lift Coefficient a L Lis the lift force t q REFS
223. dynamic and structural models together Setting FEMGRID YES writes the structural grid points in the aerodynamic coordinates along with the aerodynamic model data in the output data file This option is useful to assist in setting up the spline input Since the structural model and the aerodynamic model may contain grids that have the same identification numbers inclusion of the structural grids in the aerodynamic grids creates problems for plotting OFFSET is used to circumvent this problem by offsetting all structural grid point identification numbers with the integer of OFFSET One exception to this is for the FEMAP output file which stores the FEM grids in POINT format allowing for duplicate structure and aerodynamic grids TECPLOT FEMAP and I DEAS are commercially available graphical software programs I DEAS universal file output are data sets 781 and 780 for aerodynamic grids and aerodynamic panels respectively PATRAN is the pre and post processor of NASTRAN neutral file output are Data Blocks 403 and 404 for aerodynamic grids and aerodynamic panels respectively Structural grid points are displayed as points through Data Block 570 The ANSYS output is a FEMAP neutral file that can be read in by an ANSYS neutral file translator developed by PADT Inc also see Section 7 1 PLTAERO 4 140 DATA DESCRIPTION PLTCP PLTCP ASCII Text File Generation For Plotting the Aerodynamic Results Descriptio
224. e represents the displacement vector of a elastic or rigid body mode e is the pressure coefficient derivative with respect to 0 It should be noted that the generation of AJJ FJK and DJK matrices may be computationally costly Therefore it is recommended to save these matrices and then retrieve them for different trim analysis BULK DATA DESCRIPTION 4 27 AJJSAV 2 If SAVE SAVE the AIC matrices will be saved on an unformatted data file with file name FILENM as the archival data entity If SAVE ACQUIRE the AIC matrices will be retrieved from the data file with the name FILENM In this case a large amount of computing time can be saved 4 28 BULK DATA DESCRIPTION ALTER ALTER Perform Matrix Operation Description Performs matrix operations without modifying the program Format and Example I 2 3 4 5 6 7 8 9 10 ALTER STEP MODULE RESULT MATRIXA SYMBOL MATRIXB EE Field Contents STEP Index of operation sequence Integer gt 0 See Remark 1 MODULE Character either FEM SPLINE or GENAIC to specify the module after which the matrix operations are performed Character See Remark 2 RESULT Character string defining the name of the resulting matrix from the matrix operation Character OPERATOR Character string either INV PRINT COLATOG ROWGTOA ROWATOG or b
225. e Integer Real or Character The list of all parameters is shown in the following table NAME PARAMETER DEFAULT DESCRIPTION TYPE If any CQUAD4 CTRIA3 panel whose normal vector is toward inside of the configuration a fatal error occurs S This condition can be turned off by specifying VALUE If the distance of two corner grid points of a CQUAD4 Real 2 panel is within ELEMEPS fatal error occurs Number of CQUAD4 CTRIA3 CBAR CROD CSHEAR that are connected by a surface grid If this GRDPAN Integer 4 number of a surface grid is less than GRDPAN fatal error occurs See description of the GRID bulk data card A maximum turning angle in degrees that 1s used in the AXA search procedure to find the surface grid points This 1 NG Real 190 search procedure is used by the CAERO7 THKWING SLICE AUTOROD and AUTOBAR bulk data cards STREAM Real 1 0 x 10 Tolerance used for streamline computation If the value of y location of a grid point is less than 5 TINY the y value will be considered zero This is to Real este ensure that all grid points of a symmetric model have y 0 0 on the x z plane 4 136 BULK DATA DESCRIPTION PCHFILE PCHFILE Imports a NASTRAN Punch File Description Imports a NASTRAN Punch output file that contains the modal values of element forces stresses strains etc Format and Example 1 2 3 4 5 Ew wea me T
226. e Generation for Plotting the Interpolated Structural Mode on Aerodynamic Model Description Defines name of a data file in which the data for plotting the interpolated structural mode on the aerodynamic model are stored The PLOTMOD bulk data card is active only if the SOLUTION 1 Executive Control Command is specified Format and Example 1 2 3 4 5 PLTMODE SETID MODE TENG MAXDISP FORM FILENM conr CONT AERONM PATRAN PLOTMODE DAT AEROMODE PAT Field Contents SETID Identification number Integer gt 0 See Remark 1 SYM Symmetry condition of the structural modes corresponding to the BOUNDARY entry in the ASSIGN FEM Executive Control Command Character SYM SYM for symmetric condition SYM ANTI for anti symmetric condition SYM ASYM for asymmetric condition MODE Index of the structural modes Integer gt 0 See Remark 2 TYPE Not used MAXDISP A fraction of the reference chord defined by the REFC entry in the AEROZ bulk data card to define the maximum displacement of the mode Real gt 0 0 Default 1 0 See Remark 3 FORM FORM TECPLOT for generating the TECPLOT file FORM PATRAN for generating the PATRAN neutral results file FORM IDEAS for generating an I DEAS universal file FORM FEMAP for generating a FEMAP neutral file FORM ANSYS for generating an ANSYS supported neutral file FORM NASTRAN for generating a NASTRAN bulk data deck Char
227. e grid point define a rigid body type of motion of the aerodynamic component 4 32 BULK DATA DESCRIPTION AUTOBAR AUTOBAR Generates a Set of CBAR Description Automatically generates a set of CBAR elements between two surface grid points Format and Example 1 2 3 4 5 6 7 8 9 10 AUTOBAR EID STARTG ENDG DIRECTG AUTOBAR 100 31 31 40 Field Contents EID Unique identification number Integer gt 0 See Remark 1 STARTG Identification number of a surface grid point at which the automatically generated CBAR elements start Integer gt 0 ENDG Identification number of a surface grid point at which the automatically generated CBAR elements end DIRECTG Optional Input DIRECTG is the identification number of a surface grid point to define the initial search vector Integer 2 0 See Remark 2 Remarks 1 AUTOBAR bulk data card automatically generates a set of CBAR elements between the grid points STARTG and ENDG Automatically generated CBAR elements ENDG DIRECTG WA niti p i DIRECTG Td Search ENDG Initial START Vector START Search Vector 2 Theinitial search vector is from the grid point STARTG to the grid point ENDG The initial search vector directs the search procedure to find all grid points between STARTG and ENDG BULK DATA DESCRIPTION 4 33 AUTOROD AUTOROD Generates a Set of CROD Description Automatically gene
228. e information is very useful in instances where the program terminates due to input errors Although error messages are generated and printed in the output file the specific module in which the program terminated can be ascertained It is also useful to see the relative CPU costs of each phase of execution Typically the Aerodynamic Influence Coefficient AIC matrices generation phase printed in the logfile as GENAIC MODULE requires the most CPU time GENERATES ALL AIC MATRICES The output format for times are hours minutes seconds hundredths of a second ELASPED TIME 000 00 00 000 00 00 000 00 00 000 00 07 000 00 17 000 00 22 000 00 22 000 16 05 000 16 05 000 16 26 000 16 30 000 16 30 000 16 30 TOTAL CPU 000 00 00 000 00 00 000 00 00 000 00 07 000 00 17 000 00 22 000 00 22 000 16 05 000 16 05 000 16 26 000 16 30 000 16 30 000 16 30 Ooou 5 5onnoooo BEGIN ZONAIR LOGFILE ZONAIR INIT MODULE INITIALIZATION CNTL MODULE PROCESS CASE CONTROL IFP MODULE INPUT FILE PROCESSOR GEOMETRY MODULE ZONAIR MODEL GEOMETRY PROCESSOR CONMOD MODULE CONTROL MODES GENDYN MODULE STRUCTURAL DYNAMIC MATRICIES GENAIC MODULE GENERATES ALL AIC MATRICES SUBCASE NO 1 SOLVEM MODULE SOLVE U V W AND CP FORMOM MODULE FORCE amp MOMENT COEFFICIENTS FIELDM MODULE COMPUTES FLOW POINT SOLUTIONS END ZONAIR 000 00 00 000 00 00 000 00 07 000 00 09
229. e panels on both its upper and lower surface such as the one shown in Figure 5 8 b the wake from the wing may penetrate into the tail and creates a singularity in computation However if the tail is modeled using the CAERO7 macroelement Figure 5 19 this wake penetration problem is avoided altogether because the CAERO7 macroelement employs thin vortex and source sheets and has no thickness therefore no wake penetration from the wing into the tail can occur CR Wing 2 for tail Figure 5 19 Thin Wing Modeling for the Tail to Avoid Wake Penetration from the Wing GUIDELINES FOR AERODYNAMIC MODELING 5 11 5 7 SUPER INCLINED PANELS SUPERSONIC FLOWS In a linearized supersonic flow formulation the freestream Mach cone determines the region of influence Typical supersonic panel methods generally work well if the body under consideration is fully immersed within this region of influence However when the supersonic freestream becomes higher and or the body is relatively thick whereby a part of the body would be exposed outside of the zone of influence most supersonic panel methods would cease to be applicable For panels placed on the inlet surface Figure 5 20 a or on the nose of a thick body Figure 5 20 b the local angles of incidence on some panels would be greater than the freestream Mach cone angle this would render them lie outside of the freestream Mach cone These panels are called super inclined p
230. e spelling of SUPORT contains only one P Optional default 0 See Remark 9 PRINT n Print options to the standard output file where n is an integer Optional 0 no printout of the imported structural free vibration solution 3 4 EXECUTIVE CONTROL SECTION ASSIGN FEM Ini21 n 3 print out the structural grid point locations in the aerodynamic coordinate system print out the modal data mode shapes at the structural grid points in the aerodynamic coordinate system print out the interpolated modal data at the control points of the aerodynamic boxes in the aerodynamic coordinate system print all of the above If no PRINT is specified n 0 is used as a default Remarks Remark 1 of ASSIGN FEM At least one ASSIGN FEM Executive Control Command must exist in the Executive Control Section If the user wishes to perform the aeroelastic analysis for both symmetric and anti symmetric boundary conditions of the structural finite element model two ASSIGN FEM Executive Control Commands can be specified one with BOUNDARY SYM and the other with BOUNDARY ANTI For example ASSIGN FEM ASSIGN FEM demo1 f06 demo2 f06 FORM FORM MSC BOUNDARY MSC BOUNDARY SYM ANTI However no more than two ASSIGN Executive Control Commands can be specified Furthermore if both symmetric and anti symmetric b
231. e system since an ambiguity results BULK DATA DESCRIPTION 4 65 CPSPLN CPSPLN Wind Tunnel Measured Pressure Description Maps the wind tunnel measured pressure coefficients onto ZONAIR aerodynamic panels by spline to replace the ZONAIR computed solution Format and Example 1 2 3 4 5 6 7 8 9 10 CPSPLN IDAERO SCALE IDCOR FILEWT FORM PLTFILE CONT CONT METHOD CP SETK SETG METHOD SETK SETG CONT CONT ear etc CPSPLN 100 12 0 3 WTCP DAT TECPLOT WTCP PLT C C TPS 10 20 IPS 10 30 35 C C BEAM 50 60 70 Field Contents IDAERO If IDAERO is a positive integer it refers to the identification number of an AEROGEN bulk data card The pressure coefficients on the rigid aircraft at the flight condition defined by the AEROGEN bulk data card with ID IDAERO computed by the program are replaced by the wind tunnel measured pressure coefficients If IDAERO is a negative integer it is referred to by a TRIMINP bulk data card Integer Z 0 See Remark 1 SCALE A scale factor applying to the x y and z where the wind tunnel measured pressures are located Real gt 0 0 default 1 0 IDCOR Identification number of a CORD2R bulk data card defining a coordinate system in which the wind tunnel model is located Note that IDCOR can be a negative integer This negative sign implies that the wind tunnel model is located on the negative y
232. e to determine the wake shape The wake relaxation technique iterates the locations of the grid points on the curved wake surface until the zero force condition of the wake is satisfied This wake relaxation technique can be activated by using the RELAXW bulk data card Normal vector of upper CSHEAR GRIDU w GRIDUw Normal vector of lower CSHEAR Figure 5 9 Modeling of a Curved Wake Surface 5 4 VORTEX MODELING When a wing sustains lift flow can separate at the tip of the wing Figure 5 10 a or along the leading edge of a swept wing with sharp edges Figure 5 10 b This separation produces vortex sheets that roll up into strong vortices that are shed downstream Studies of the principal vortex indicate that the vortex roll up shape and strength are relatively independent of viscosity and can be modeled as potential flow Two types of roll up vortex can be modeled in ZONAIR using a line vortex element by the CROD bulk data card and a vortex roll up sheet by the VORNET bulk data card a Vortex Roll Up at Wing Tip b Vortex Roll Up at Wing Leading Edge Figure 5 10 Vortex Roll Up on a Lifting Wing 5 6 GUIDELINES FOR AERODYNAMIC MODELING The line vortex element approximates the roll up vortex by lumping the vortices containing the roll up vortex sheet into line segments Figure 5 11 shows a typical modeling of these line vortex segments or CROD elements along a wing tip GRIDO CROD GB Figure 5 11 CRO
233. eature provides tremendous savings in CPU time associated with the re running of jobs This feature is very useful when the changes are made to the flight conditions f q r the structural model spline input or the static aeroelastic trim solution e g if solution is desired for a different density altitude However in cases where changes to the aerodynamic model or input parameters in the MACH bulk data card are required the AIC matrices must be recomputed 2 06 ZONAIR SCRIPT FILE The ZONAIR script file is used to submit jobs to be run by the ZONAIR software system and is located in the ZONAIR home directory Multiple jobs can be submitted at one time on both UNIX and PC systems This script file can be executed from any directory on the host system with the appropriate environment variables set The environment variables are normally set up automatically during installation of the ZONAIR software system but can be set up manually see Installation Notes for details on how to adjust environment variables Two versions of the ZONAIR script file are available The first developed for the UNIX environment is written in the C shell scripting language The second developed for the PC environment is written in FORTRAN and is provided in executable format The following two sections provide instructions on submitting multiple ZONAIR jobs and step by step descriptions on the steps taken by UNIX and PC versions of the ZONAIR script file
234. ececececececececececececeeesecs 6 2 6 2 SPLINE FOR DISCONTINUOUS STRUCTURE eese hne nennen nnn nnn 6 3 6 3 ENSURING CONTINUOUS STRUCTURE ACROSS TWO ADJACENT CAERO7 MAGROELEMBENIS 5 E E ee e e ER Tee o t d Rede 6 4 6 4 ACCURATE ROTATIONAL STRUCTURAL DISPLACEMENT FOR BEAM SPLINE METHOD 6 5 6 5 INACCURATE SPLINE RESULTS DUE TO 6 5 PEOTEILES 25 cda 7 1 741 AERODYNAMIC MODEL 11020222 2 2 3 000000000000000000000000000000005000 7 2 7 2 PRESSURE COEFFICIENTS PLTQCP esses enne entente enne nennen enne 7 8 7 3 INTERPOLATED STRUCTURAL MODE SHAPE PLTMODE seen 7 14 7 4 STATIC AEROELASTIC TRIM ANALYSIS RESULTS PLTTRIM eee 7 20 ii FOREWORD ZONAIR UPGRADES This section lists the enhancements made to the ZONAIR software system Version 4 4 Enhancements 1 The THERMAL bulk data card has been modified to allow the aeroheating analysis with structural flexibility effects by referring to a FLEXLD bulk data card A new chapter Chapter 9 has been added into the Applications Manual This chapter describes how to perform an aeroheating analysis with structural flexibility effects of a missile like configuration In the FLEXLD bulk data card an option
235. ectangular coordinate system by reference to three grid points These points must be defined in coordinate systems whose definition does not involve the coordinate system defined The first point is the origin the second lies on the z axis and the third lies in the plane of the x z plane Format and Example Ji 2 3 4 5 6 7 8 9 10 Field Contents CID Coordinate system identification number Integer gt 0 Gi Grid point identification number can be either a surface grid or a reference grid Integer gt 0 G1 G2 63 Remarks 1 Coordinate system identification numbers on all CORDIR CORDIC CORDIS CORD2R CORD2C and CORDOS entries must be unique 2 The three points G1 G2 and G3 must be noncollinear 3 The location of a grid point P in the sketch in this coordinate system 1s given by X Y Z where 0 is measured in degrees 4 displacement coordinate directions at P are shown above by ux Uy u 5 Oneor two coordinate systems may be defined on a single entry BULK DATA DESCRIPTION 4 57 CORDIS CORDIS Spherical Coordinate System Definition Form 1 Description Defines a spherical coordinate system by reference to three grid points These points must be defined in coordinate systems whose definition does not involve the coordinate system defined The first point is the origin the second lies on the z axis and the third lies in the plane of the azimuthal origin Format and Example
236. ed to import the structural finite element solution and to activate of spline module respectively Format FLEXLD n Example FLEXLD 100 Remarks 1 FLEXLD Case Control Command must appear within a subcase section i e between two SUBCASE Case Control Commands 2 The integer n is the identification number FLEXLD bulk data card Integer gt 0 This FLEXLD bulk data card must exist in the Bulk Data Section 3 FLEXLD and n must be separated by an equal sign 3 30 EXECUTIVE CONTROL SECTION MEMORY MEMORY Allocable Maximum Memory Description Defines the maximum memory in terms of megabytes MB that is allocable by ZONAIR from the computers heap space memory Format MEMORY nMB Example MEMORY 32MB Remarks 1l The MEMORY command is optional If no MEMORY command is specified the default value is 80 megabytes 80MB 2 nMB represents an integer followed by the characters MB 3 ZONAIR dynamically allocates memory within the computers heap space memory for matrix operations For large matrices ZONAIR will occupy a large portion of the heap space for in core matrix operations This may degrade the performance of other jobs that are simultaneously running on the computer To circumvent this problem it is recommended that the MEMORY command be used to define the maximum allocable memory by ZONAIR so that the out of core matrix operations are employed for large matrices In this case
237. effects can be included by only evaluating the exact integral solution along each line segment line segment line segment Figure 1 5 Line Segments for Wake Modeling 14 NASTRAN BULK DATA INPUT FOR ZONAIR ZONAIR input is very similar to the NASTRAN bulk data input In fact some NASTRAN bulk data cards can be directly adopted for ZONAIR modeling Also multiple subcases can be specified in one ZONAIR job for different flight conditions This direct adoption of some NASTRAN bulk data cards for ZONAIR modeling is shown in Figure 1 6 INTRODUCTION 1 3 ECHO SORT SUBCASE 1 TITLE naca 151 07 wing body test case the last model CBAR AERO 1 SUBCASE 2 AERO 2 BEGIN BULK f Wake Modeling CBAR 483 1 271 282 CBAR 484 1 273 283 Grid Point Locations GRID 1 000 000 000 GRID 586 29 313 12 000 000 Triangular Panels CTRIA3 1 1 2 2 3 CTRIA3 6 1 X 7 8 Quadrilateral Panels CQUAD4 7 1 2 9 10 eni KERENDAN ENEE EE EEREN 9 CQUAD4 558 1 193 200 201 271 DES SN N 8 Wing Tip Line Vortex e SS CROD 580 1 586 568 SEN Ud b Wake on Body Impingement Behind Wing Body Junction T gn RBE2 1001 51 52 aye eS __ SS 211 311 412 963 319 ENDDATA 222 1 5 Figure 1 6 NASTRAN Bulk Data Input for ZONAIR PANEL MODEL GENERATION Figure 1 7 presents the comparison between ZONAIR unstructured paneling scheme and PANAIR s paneling
238. eir associated output files 4 2 7 MISCELLANEOUS INPUT Name Description Remarks Used to insert comments into the Bulk Data Section Optional AEFACT Specifies a list of real numbers Optional ALTER Perform Matrix Operations Optional CORDIC Cylindrical coordinate system definition Form 1 Optional CORDIR Rectangular coordinate system definition Form 1 Optional CORDIS Spherical coordinate system definition Form 1 Optional CORD2C Cylindrical coordinate system definition Form 2 Optional CORD2R Rectangular coordinate system definition Form 2 Optional CORD2S Spherical coordinate system definition Form 2 Optional DMI Header of direct matrix input Optional DMIG Direct matrix input at structural finite element grid points Optional DMIL Defines the values of matrix elements by 16 column fields Optional DMIS Defines the values of the matrix elements by 8 column fields Optional ENDDATA To signify the end of the Bulk Data Section Required GRIDFRC vue t force at a set of a structural finite element Optional INCLUDE Inserts an external file into the Bulk Data Section Optional LOADMOD 5 2 e 2 of structural grid points for Optional OMITMOD Delete structural modes Optional OUTPUT4 s i matrix data entity in the OUTPUTA format to a Optional PARAM Alters values for parameters used in the computation Optional comme IU eee Defines a list of identific
239. el Integer gt PANEL1 See Remark 3 Remarks 1 PANLSTI is referred to by SPLINEi ATTACH LOADMOD JETFRC and or AESURFZ bulk data card 2 MACROID is used to define a spline plane for the infinite plate spline method SPLINE1 bulk data card 3 The following sketch shows the panels identified via PANEL1 and PANEL2 entries if PANELI 111 PANEL2 118 and MACROID 111 BULK DATA DESCRIPTION 4 133 PANLST2 PANLST2 Set of Aerodynamic Panels Description Defines a set of aerodynamic panels Format and Example 1 2 3 4 5 6 7 8 9 10 PANLST2 MACROID PANEL1 PANEL2 PANEL3 PANEL4 PANEL5 PANEL6 CONT Field Contents SETID Set identification number Integer gt 0 See Remark 1 MACROID Identification number of a CAERO7 BODY7 or MATBODY bulk data card to which the aerodynamic panels listed in the set belong Integer gt 0 PANEL1 Identification number of aerodynamic panels Integer gt 0 See Remark 2 Remarks 1 PANLST2 is referred to by SPLINEi ATTACH LOADMOD JETFRC and or AESURFZ bulk data card 2 Field number 5 can be a character string THRU This implies that all aerodynamic panels with identification numbers starting with PANEL and ending with PANEL3 are included in the list 3 IfPANLST2 is not referred to by the SPLINE1 bulk data card multiple PANLST2 bulk data cards with the same SETID are allowed In this case all aerodynamic panels listed in
240. en the aerodynamic model and the structural finite element model for displacement and force transferal Specifically the spline input generates a spline matrix that attaches every aerodynamic panel to a set of structural finite element grid points Here the aerodynamic panels represent the discretized aerodynamic model that is defined by the aerodynamic geometry input The structural finite element grid points are imported through the external file specified in the ASSIGN FEM Executive Control Command BULK DATA DESCRIPTION 4 7 The following table presents the bulk data cards for the spline input Name Description Remarks ATTACH Defines a rigid body connection between aerodynamic panels Optional and structural finite element grid points PANLSTI Defines a set of aerodynamic panels region defined by 2 Optional aerodynamic panel identification numbers PANLST2 Defines a set of aerodynamic panels region defined by individual aerodynamic panel identification numbers Optional but all aerodynamic panel identification Defines a set of aerodynamic panels region defined by the numbers must be PANLST3 entry LABEL in the CAERO7 BODYT or MATBODY bulk uniquely and data card completely listed in PANLSTI PANLST2 and or PANLST3 SET2 Defines the aerodynamic macroelements in term of spanwise Optional and chordwise points zone for spline SPLINEO Impos
241. er 1s the identification number of an EXTFILE bulk data card where the filename is specified This feature allows for filenames up to 72 characters to be input Character or Blank See Remark 4 Character string up to 16 characters to specify the filename to store the interpolated Cp and Mach numbers of the surface boxes Character or Blank See Remark 5 The name of a data file in which the aerodynamic model is stored in a PATRAN neutral file ONLY USED IF FORM PATRAN If the first character of AERONM starts with a dollar sign the rest of the characters must be integers This integer is the identification number of an EXTFILE bulk data card where the filename 15 specified This feature allows for filenames up to 72 characters to be input Character Default See Remark 7 1 The INPCFDI bulk data card is used to import the CFD solution from an unstructured CFD code This feature allows ZONAIR to compute more accurate incremental aeroelastic loads due to structural flexibility effects using CFD generated rigid loads 2 Because the CFD mesh may be oriented in an arbitrary fashion with respect to the ZONAIR aerodynamic model it is required to transform the CFD mesh so that the CFD surface mesh and the ZONAIR aerodynamic model overlap with each other This can be achieved by introducing a CORD2R bulk data card with identification number TRANSF that defines a coordinate system where the CFD mesh is
242. er string up to 8 characters used to define the thin wing component Character Identification number of ACOORD specifying a local coordinate system and orientation bulk data card Integer gt 0 or blank Default 0 See Remark 2 Number of spanwise divisions of the thin wing component Integer 2 2 Number of chordwise divisions of the thin wing component Integer 2 2 Identification number of AEFACT bulk data card used to specify the spanwise divisions of the thin wing component in percentage of the wing span The number of values listed in AEFACT must be NSPAN and must start with 0 0 and end with 100 0 If LSPAN 0 then NSPAN evenly distributed spanwise divisions are used Integer 2 0 See Remark 3 Identification number of a PAFOIL7 PAFOILS bulk data card to specify sectional airfoil coordinates If PAFOIL7 0 it is assumed that the CAERO7 wing component is a flat plate Integer 2 0 Not Used X Y and Z location of the root chord leading edge Real Length of the root chord Real 4 46 BULK DATA DESCRIPTION CAERO7 ATTR LRCHD RWAKE XIL YTL ZTL TCH ATTT LTCHD TWAKE Remarks Character string either YES or NO For ATTR YES the root the thin wing component is attached to is a body component represented by CQUAD4 CTRIA3 or BODY7 bulk data cards Character For ATTR NO LRCHD is the identification number of an AEFACT bulk data card used to specify the
243. erance used to detect the above two conditions BULK DATA DESCRIPTION 4 167 SPLINEF SPLINEF Spline Matrix for Force Mapping Description Generates the force spline matrix to map the aerodynamic forces at the aerodynamic grids to the structural grids by altering the SPLINE1 SPLINE2 or SPLINE3 bulk data card Format and Example 1 2 3 4 5 6 7 8 9 10 SPLINEF i Field Contents EID Identification number that is used only for error message output Integer gt 0 See Remark 1 IDSPLINE Identification number of a SPLINE1 SPLINE2 or SPLINE3 bulk data card whose entry SETG is replaced the 5 entry of the SPLINEF bulk data card Integer 70 See Remark 2 SETI Identification number of a SET1 or SETADD bulk data card to list a set of identification numbers of structural grid points that are used to generate the force spline matrix Integer 70 See Remark 3 Remarks 1 The SPLINEF bulk data card is optional Its existence triggers the program to generate a different force spline matrix from the displacement spline matrix There are two spline matrices generated by the spline module In UGTKG x UGFRC F where x is the G set displacement at the structural grid points h is the k set displacement at the aerodynamic boxes F4 is the aerodynamics forces at the aerodynamic boxes E is the G set forces at the structural grid points UGTKG 1s the d
244. ero grids Steps within PATRAN to View the Deformed or Animated interpolated Mode Shape ZONAIR output file generated by PLTMODE bulk data card Open anew PATRAN database Read in the geometry file first Select File Import from the Radio buttons Object Model Source Neutral select the appropriate geometry neutral file and click Apply Read in the displacement results file next Select File Import from the Radio buttons Object Results Source Patran2 dis After selecting the Patran2 dis locate the ZONAIR interpolated mode shape displacement results file in whatever directory it has been stored in Select the appropriate displacement results file and click Apply Verify that the import read was successful in the Dialog Box Select Results from the Radio buttons Action Create Object Quickplot The Fringe results list should show up results that were read in The following PATRAN results template can be used to load the displacements from ZONAIR ZONAIR dis res tmpl KEYI PATRAN 2 5 results file template for ZONAIR dis files LOC 0 TYPE vector COL PRI SEC UMN 1 2 3 Displacements Translational PE nodal TYPE END Tecplot Compatible Output A sample of the Tecplot compatible output is shown in the following figure and is described below TITLE THE 1TH MODE ON AERO MODEL FROM FILE sample fre VARIABLE X Y Z EXTID ZONE I 260 J
245. erodynamic pressures computed by the AEROGEN bulk data card on the rigid aircraft by the wind tunnel measured aerodynamic pressures FOREWORD 1 ZONAIR UPGRADES 3 A new bulk data card called TRIMINP is incorporated in the trim module to replace the program computed derivatives of the aerodynamic forces of a trim variable by the user supplied values The TRIMINP bulk data card is referred to by the TRIMVAR bulk data card where the user supplied values are imported by the INPCFD INPCFD2 or CPSLIN bulk data card 4 Two new chapters Chapter 7 and Chapter 8 are included in the Applications Manual Chapter 7 documents a trim analysis of the AGARD 445 6 wing case where the program computed aerodynamic forces of the rigid aircraft are replaced by the user supplied values The user supplied values are obtained by the CFD analysis and the wind tunnel measurement Chapter 8 shows the modeling guidelines for modeling complex configurations Four whole aircraft configurations are included in Chapter 8 A 380 F 15 F 18 and a conceptual design aircraft FOREWORD 2 1 1 Chapter 1 INTRODUCTION WHAT IS ZONAIR ZONAIR is an engineering software system that utilizes a unified high order subsonic supersonic hypersonic panel methodology as the underlying aerodynamic force generator to efficiently create aerodynamic and loads databases for 6 d o f simulation and critical loads identification ZONAIR is formulated based on the unstructu
246. es zero displacement condition on aerodynamic panels Optional Defines a surface spline method Infinite Plate Spline method SPLINEI for CAEROT Optional Defines a beam spline method for CAERO7 BODY7 SPLINE2 CQUADA CTRIA3 Optional Defines a 3 D spline Thin Plate Spline method for CAERO7 SPLINES BODY7 CQUAD4 CTRIA3 enone SPLINEF Spline matrix for force mapping Optional SPLINEM Saves or retrieves the spline matrix Optional It should be noted that all identification numbers of the aerodynamic panels must be uniquely and completely specified in the PANLST1 PANLST2 and or PANLST3 bulk data cards Violation of this condition results in fatal errors as following FATAL ERROR AERODYNAMIC PANEL WITH ID xxxx IS NOT ATTACHED TO FEM MODEL This indicates that the aerodynamic panel with identification number xxxx is not specified in the PANLSTI PANLST2 and or PANLST3 bulk data cards 4 8 BULK DATA DESCRIPTION FATAL ERROR AERODYNAMIC PANEL WITH ID xxxx HAS BEEN SPLINED MORE THAN ONCE This indicates that the aerodynamic panel with identification number xxxx is repetitively specified in the PANLST1 PANLST2 and or PANLST3 bulk data cards Figure 4 3 depicts the interrelationships of the bulk data cards for spline SPLINE1 SPLINE2 SPLINE3 ATTACH SPLINEO Infinite Plate Spline Beam Spline 3 D Spli
247. esired airfoil shape at the wing root 1s shown in a below and a positive value for ITAX were used the resulting airfoil shape would be that shown in b which is incorrect In this case a negative value for ITAX is required to generate the airfoil shape shown in a 4 130 BULK DATA DESCRIPTION PAFOIL7 E a b Note The number of x coordinate values must be at least 3 The values listed in the AEFACT bulk data cards with identification numbers of ITH R T ICAM R T and RAD R T are in percentage of the root tip chord lengths c respectively For instance in the following figure the ITHR represents the half thickness distribution computed by t c 100 where t is the half thickness and c is the chord at the root The ITHT represents similar values at the tip chord ICAM R T and RAD R T similarly denote camber and leading edge radius computed by their respective equations shown in the figure below Root or Tip Chord Half Thickness t ITHR ITHT t c x 100 0 Camber Zi ICAMR ICAMT 2 x 100 0 Wing Mean Plane Leading Edge Raduis r RADR RADT r c x 100 0 Note The positive camber is in the same direction of the normal vector of the CAERO7 macroelement See Remark 6 of the CAERO7 bulk data card for the definition of the normal vector The number of values listed in the AEFACT cards for ITAX ITHR ICAMR ITHT and ICAMT must be the same The camber and th
248. f freedom of the control force 1 2 and 3 represent the forces along the x y and 7 directions respectively 4 5 and 6 represent the moments about the x y and z directions respectively Integer gt 0 See Remark 3 FACTOREi Multiplication factor Real Any character string with no embedded blanks to describe the control force Remarks 1 GRIDFRC can be selected as a control force for the TRIM analysis 2 degrees of freedom of the force or moment are defined in the output displacement coordinates of the grid in the structural finite element model i e the local coordinate system for displacements of the structural finite element grid 3 The units of forces and moments are FMMUNIT FMLUNIT sec and FMMUNIT FMLUNIT sec respectively where FMMUNIT and FMLUNIT are defined in the AEROZ bulk data card 4 98 BULK DATA DESCRIPTION INCLUDE INCLUDE Insert an External File into the Bulk Data Section Description Inserts an external file into the Bulk Data Section The INCLUDE statement may appear anywhere within the Bulk Data Section of the input deck Format and Example INCLUDE filename The following INCLUDE statement is used to obtain the Bulk Data from another file called External dat BEGIN BULK INCLUDE External dat ENDDATA Field Contents filename Physical filename of the external file to be inserted The user must supply the name according to installation or m
249. f these reference grids behind CNTLX at j 4 and 5 shown in the figure are located along a straight line whose direction is SLOPE BULK DATA DESCRIPTION WTIAJJ WT1AJJ Force Moment Correction Matrix Description Corrects the Aerodynamic Influence Coefficient AIC matrix by a force correction matrix so that the forces and moments computed by the corrected AIC matrix match a given set of component forces and moments Format and Example 1 2 3 4 5 9 10 WTlAJJ IDMK KINDEX METHOD WTLFILE CONT Field Contents IDMK Identification number of AEROGEN bulk data card whose generated AIC matrix is to be corrected Integer gt 0 See Remark 1 SYM Character string either SYM ASYM or ANTI to specify the symmetric condition of the matrix that is to be corrected by the downwash weighting matrix Character SYM SYM for symmetric condition SYM for anti symmetric condition SYM ASYM for asymmetric condition KINDEX Not Used METHOD Not Used WTIFILE WTIFILE is a character sting representing the name of the output file that contains the computed force correction matrix If the first character starts with a dollar sign the rest of the characters must be integers This integer is the identification number of an EXTFILE bulk data card where the filename is specified This feature allows for filenames up to 72 characters to be input Character or Blank
250. file translator developed by PADT Inc also see Section 7 3 PLTMODE PATRAN requires that the aerodynamic model be stored in a neutral file and that analysis results be stored in a results file Therefore the AERONM entry is used to assign a name for a neutral file that contains the aerodynamic model while the FILENM entry specifies a file that will contain the displacement results For more details please see Section 7 3 PATRAN Compatible Output 4 144 DATA DESCRIPTION PLTSURF PLTSURF ASCII Text File Generation for Plotting the Aerodynamic Control Surface Description Defines name of a data file in which the data for plotting the deflected aerodynamic control surface on the aerodynamic model are stored Format and Example 1 2 3 4 5 6 7 8 9 10 PLTSURF SETID LABEL MAXDISP FORM FILENM AERONM EN PLTSURF RUDDER PATRAN PLOT PLT AEROMODE PLT Field Contents SETID Identification number Integer gt 0 See Remark 1 LABEL Character string that matches the LABEL entry of an AESURFZ bulk data card Character See Remark 2 MAXDISP A factor to amplify the deflection of the control surface Real gt 0 0 Default 1 0 FORM FORM TECPLOT for generating the TECPLOT file FORM PATRAN for generating the PATRAN neutral results file FORM IDEAS for generating an I DEAS universal file FORM FEMAP for generating a FEMAP neutral file FORM ANSYS for generating an ANSYS supported
251. for the wake modeling in ZONAIR the flat wake and the curved wake CBAR Figure 5 7 Flat Wake Modeling by CBAR Elements Figure 5 3 1 depicts two flat wake surfaces whose leading edges are attached to the grid points at the trailing edges of the upper and lower surfaces of a wing The trailing edge of the wake surface is extended to infinity The flat wake surface is always parallel to the x axis of the aerodynamic coordinate system The wake effects are represented by the potential difference between the doublet strength on the upper wake surface and on the lower wake surface Because the doublet strength is constant on the wake surface and the wake surface is flat which greatly simplifies the wake integral an exact integral solution can be obtained for the wake integral by integrating the doublet kernel integral from the trailing edge of the wing to infinity on the flat surface This exact integral solution is only a function of the doublet strength at the grid points along the trailing edge of the wing i e the wake effects are included by evaluating the exact integral solution along the line segments at the trailing edge of the wing ZONAIR models these line segments by the CBAR bulk data cards Therefore ZONAIR does not require the modeling of the flat wake surface which greatly reduces the modeling effort for wake modeling Because the accuracy of the aerodynamic results on the wing usually has little influence fro
252. ger 0 See Remark 1 Identification number of a surface grid point that is located at the trailing edge of the wing tip from which the slicing action starts Note that STARTG can be a negative integer In this case the grid STARTG is not split into upper and lower grid points Integer Identification number of a surface grid point at which the slicing action for the trailing edge ends STARTG and ENDBG must be located at the trailing edge of the wing Integer See Remark 2 Optional input DIRECTI is the identification number of a surface grid point to define the initial search vector to slice the trailing edge Integer gt 0 Character string either YES NOCBAR or NO If RBE2 YES or NOCBAR a RBE2 element is automatically generated for handling the trailing wake behind the wing body junction Please refer to the RBE2 bulk data card for detailed description Character Default YES See Remark 3 Identification number of a surface grid point at which the slicing action for the wing tip ends STARTG and ENDRG must be located at the wing tip edge Integer See Remark 3 Same as DIRECT but for the wing tip Integer gt 0 Character either YES or NO If SPLIT YES the ENDRG grid point is split into upper and lower grid points Characters Default NO See Remark 4 1 The objective of the SLICE bulk data card is to automatically convert a wing like panel model with closed wing t
253. gt 0 See Remark 5 Character string either SET1 COS or EVEN to define the locations of the NFED points along the ith roll up vortex line Note that for DIVIDE NFED number of reference grid points will be internally generated by the program whose identification numbers start from REFSTRT and incrementally increase by one Character See Remark 6 For DIVIDE SETI IDSET is the identification number of a SET1 bulk data card that lists NFED identification numbers of reference grid points defined by the GRID bulk data card with entry PS 0 Also for DIVIDE SET1 the entries REFSTRT ROLLUP and REFGRID are not used For DIVIDE SET1 IDSET is the identification number of a reference grid point where the ith roll up vortex line ends Integer gt 0 See Remark 7 An integer to define the identification number of those reference grid points internally generated by the program The identification of the first reference points along the ith roll up vortex line is REFSTRT and the last point is REFSTRT NFED 1 Note that REFSTRT must be properly assigned so that among all reference grid points no duplicated identification number occurs Integer gt 0 Character string either LINE or CIRCLE to define the shape of the ith roll up vortex line Character Default CIRCLE See Remark 8 Identification number of a reference grid point to define a plane where the
254. gure 5 18 shows a wing tail configuration modeled by two macroelements If the wing and tail are located in the same plane coplanar all spanwise divisions of the tail must be aligned with those of the wing violation of this requirement results in the vortex lines shed from the wing that cut through the aerodynamic boxes of the tail Since at the vortex line the aerodynamic influence is singular this yields an unrealistically large downwash effect on the tail In fact if a vortex line of the wing were to align with a control point on the tail the aerodynamic matrix would become singular This modeling restriction is still required for the case where the wing and the tail are not located in the same plane and the distance d along the normal direction is small 1 0 d This restriction can be relaxed only if the distance is larger than the width of the strip w see Figure 5 18 b 5 10 GUIDELINES FOR AERODYNAMIC MODELING Strip Width I Wing Wake Region i I t d T V 1 1 Note Distance in the normal Yyyy direction 0 for co planar case a Top View b Front View Figure 5 18 Alignment of Spanwise Divisions of a Wing Tail Configuration Modeled by two CAERO7 Macroelements Another configuration where the use of thin wing modeling is recommended is the coplanar wing tail configuration If the tail is modeled exactly by the surfac
255. hat can be included in the bulk data input the surface grid points and the reference grid points where Surface grid point a point located on the surface of the aerodynamic model which is discretized by the CQUADA and or CTRIA3 panels This implies that a surface grid point must be a corner point of the CQUAD4 CTRIA3 panels surface grid point that is not attached to any CQUAD4 CTRIA3 panel gives fatal error 4 96 BULK DATA DESCRIPTION GRID Reference grid point A point usually used to define the CSHEAR panel for wake modeling Because the potential on the CSHEAR panel is equal to the potential at the surface grid points where the wake surface starts The reference grid point does not introduce additional unknowns to the problem Also the reference grid point can be used as a dummy point for defining a local coordinate system by the CORDIR CORDIS or CORDIC bulk data card Note Except being the corner point of three panels each surface grid point must be at least the corner point of four panels elements For instance four CQUAD4 CTRIA3 panels as shown in Figure a two CQUAD4 CTRIA3 panels and two CBAR elements as shown in Figure b one CQUAD4 CTRIA3 panel one CROD element and one CBAR element with an infinite line vortex PA or PB entry gt 0 as shown in Figure c Surface grid Surface grid Surface grid SSS LARS zt CROD 7 infinite line vortex a b c The above condition
256. he TECPLOT output is in Tecplot s finite element zone input format The I DEAS output is in universal data file format The FEMAP output is in FEMAP neutral file format The ANSYS format is identical to the FEMAP neutral file output format and can be read into ANSYS via a translator developed by PADT Inc in Tempe Arizona Note that the ANSYS option description is not included in this Chapter since it is identical to the FEMAP output option Excel output is in column format and can be read in by virtually any spreadsheet application Finally the NASTRAN supported output is in bulk data format and can be plotted by any graphical software package capable of reading in and displaying NASTRAN bulk data input e g ARIES FEMAP etc The following sections describe each of the output plot files listed above Samples of each output file taken from the cropped wing and trim forward swept wing demonstration test cases are presented along with descriptions of the output file contents 7 1 AERODYNAMIC MODEL PLTAERO An output data file of the aerodynamic model can be generated with the PLTAERO bulk data card see Figure 7 1 Viewing the aerodynamic model is extremely useful in determining if the aerodynamic configuration is modeled properly Often times numeric typos are entered in the bulk data input that can go undetected in the analysis For example an aerodynamic coordinate system that is referred to by an underwing store may be located in the wrong pl
257. he overall flow structure Due to the attached flow assumption of potential flow theory the best panel model is one in which all panels are placed on the closest streamlines of the flow to the body surface not on the exact surface of the configuration For instance the flow velocity predicted by the potential flow passing a sharp corner would be infinite at the corner in order to keep the flow attached Shown in Figure 5 21 a is a flow passing a forward facing step where a vortex is developed and trapped at the corner and a streamline is developed over the trapped vortex If the surface of the step is modeled exactly by aerodynamic panels Figure 5 21 b an infinite velocity will be predicted by the panel method which obviously is incorrect The recommended panel modeled is shown in Figure 5 21 c where the panels are placed on the streamline to form a smooth panel model In so doing the flow velocity on this smooth panel model can remain finite In fact ZONAIR does not allow any panel whose inclination angle with respect to the flow direction to be greater than 90 to avoid such an infinite flow velocity prediction such as the one shown in Figure 5 21 b Similarly the correct panel model for a flow passing a backward facing step is shown in Figure 5 21 c Infinite velocity e flow Stream line W Panel on stream line Vortex a Real Flow b Incorrect Panel Model c Correct Panel Model Figure 5 21 Modeling of Flow Passing a Forward Fa
258. he VIS DENS VEL PRES entries Real or Characters TYPE Character to define the vortex model Character Default LAMB See Remark 2 A Radius of the viscous core Real gt 0 0 VIS Viscosity in FMMUNIT FMLUNIT Sec where FMMUNIT and FMLUNIT are the mass and length units defined in the AEROZ bulk data card Required only if ALT NONE Real Default 2 59e 09 slinch inch s DENS Density in FMMUNIT FMLUNIT 3 Required only if ALT NONE Real Default 1 14e 07slinch inch 3 VEL Freestream velocity in FMLUNITS Required only if ALT NONE Real Default 12000 inch sec PRES Pressure in FMUNIT FMLUNIT Sec Required only if ALT NONE Real Default 14 69 Ibf in Remarks 1 VISCOUS bulk data card is referred to by a MACH bulk data card Once VISCOUS is specified in the MACH bulk data card the aerodynamic forces and moments due to skin frictions employ the viscous vortex model which can avoid the singularity at the center of the inviscid line vortex elements 2 following figure shows that the CROD element generates the induced velocity as a function of r 4 202 BULK DATA DESCRIPTION VISCOUS Viscous CROD core radius For an inviscid vortex model the induced velocity is a function of 1 r which is singular at r 0 The VISCOUS bulk data card introduces a viscous core model to circumvent this singularity problem For TYPE LAMB the Lamb s model is used T
259. he X Y plane if CID gt 0 or the X Z plane if CID lt 0 defines the mean plane of the control surface 4 26 BULK DATA DESCRIPTION AJJSAV AJJSAV Save or Retrieve the Aerodynamic Influence Coefficient Matrix for Stability Derivatives Description Save or retrieve the Aerodynamic Influence Coefficient AIC matrix associated with an AEROGEN bulk data card for aerodynamic stability derivatives or flexible loads generation Format and Example 1 2 3 4 5 6 7 8 9 10 AJJSAV IDAERO SAVE FILENM AJJSAV 10 ACQU FAIC dat Field Contents IDAERO An integer that matches the IDAERO entry of the AEROGEN bulk data card whose generated AIC matrix is to be saved or retrieved Integer gt 0 See Remark 1 SAVE Save the AIC matrices generated by the AEROGEN bulk data card with identification number being equal to IDAERO to file FILENM or retrieve AIC from FILENM Characters or blank SAVE SAVE saves the AIC data SAVE ACQUIRE retrieves an existing file containing the AIC data Otherwise do not save or retrieve data FILENM File name up to 16 Characters to specify the file name on which the AIC data is saved or retrieved Character or Blank See Remark 2 Remarks 1 compute the aerodynamic stability derivatives or the flexible loads it is required to generate three matrices namely AJJ FJK and DJK shown as follows 27 IoT tel wher
260. he induced velocity is shown as follows oe where is the freestream velocity defined by the VEL entry u is defined in the VIS entry and L is the length of the line vortex starting from the grid point specified in the GRIDO entry of the CROD bulk data card For TYPE SCHL the Schlinker s model is used The induced velocity is shown as follows A V 2 1 1 25649 y 2 1 e x r E where a is the radius of the viscous core defined in the A entry For TYPE MCCR the McCroskey s model is used The induced velocity is shown as follows A Vr BULK DATA DESCRIPTION 4 203 VORNET VORNET Macroelement for Vortex Roll Up Model Description Defines a macroelement to automatically generate a set of CSHEAR CROD and CBAR elements for the modeling of a vortex roll up sheet Format and Example 1 2 3 4 5 6 7 8 9 10 VORNET IDVOR LABEL TIPGRID NFED NTIP NWAKE CBAR CONT CONT GRIDU GRIDL DIVDE IDSET REFSTRT ROLLUP REFGRID CONT CONT etc ere CONT CONT GRIDU GRIDLy DIVIDE IDSETy REFSTRTy ROLLUPy REFGRIDy N NTIP NFED VORNET 100 VORTEX 101 10 4 0 1 YES V V 101 201 EVEN 401 10001 CYCLE 301 V V 102 202 SET1 10 V V 40001 40001 CDS 402 20001 LINE Field Contents IDVOR Identification number Integer gt 0 See Remark 1 LABEL An arbitrary character
261. he number of trim degrees of freedom including both free and 4 180 DATA DESCRIPTION TRIM given trim degrees of freedom the trim system is defined as determined trim system since the number of equations and unknowns are equal If the total number of unknowns is greater than the number of trim degrees of freedom the trim system is defined as over determined trim system Solving the over determined trim system requires the minimization of a user defined objective function a TRIMOBJ bulk data card referred to by the IDOBJ entity of the TRIM bulk data card while subjected to a set of user defined constraint functions a TRIMCON bulk data card that is referred to by the IDCONS entity of the TRIM bulk data card If the total number of unknowns is less than the number of trim degrees of freedom the trim system is unsolvable and a fatal error will occur BULK DATA DESCRIPTION 4 181 TRIMADD TRIMADD Defines a Trim Function as a Function of Other Trim Functions Description Defines a trim function as a function of other trim functions The function is expressed as E E E F esas o 5 ZLI Pos where represents s or Format and Example Field Contents IDFNC Unique identification number among all TRIMFNC and TRIMADD bulk data cards Integer gt 0 See Remark 1 So Real coefficients shown in the above equation Real Fo Identification number of
262. he thin wing component Integer 2 0 1 CAERO7 represents a thin wing component where a sheet of vortex and source singularities is distributed on the main plane of the thin wing The vortex singularity models the lifting effects and source singularity models the thickness effects of the thin wing component 2 All coordinate locations defined above in XRL YRL ZRL XTL YTL and ZTL are in the local wing coordinate system defined by the ACOORD bulk data card 3 The number of spanwise and chordwise divisions of the thin wing component includes the end points therefore there will be NSPAN 1 spanwise strips NCHORD 1 chordwise strips NSPAN x NCHORD aerodynamic grids and NSPAN 1 NCHORD 1 aerodynamic panels generated by each CAERO7 bulk data card Among all aerodynamic grids and panels of the CAERO7 BODY7 CTRIA3 and BULK DATA DESCRIPTION 4 47 CAERO7 CQUADA bulk data cards no duplicate identification number is allowed following figure demonstrates the numbering scheme In the example given below a CAERO7 has WID 101 NSPAN 5 and NCHORD 4 There are 5 1 4 1 12 aerodynamic panels and 5 x 4 20 aerodynamic grid points generated for this lifting surface Wing panels are numbered starting with the wing id of 101 and ending at 112 Wing aerodynamic grid points are numbered starting with the wing 1d of 101 and ending at 120 duplicate identification number 1 e aerodynamic panel s and aerodynamic grid
263. here the filename is specified This feature allows for filenames up to 72 characters to be input Character or Blank 4 190 DATA DESCRIPTION TRIMINP Remarks 1 The TRIMINP bulk data card is referred to by the TRIMVAR bulk data card pressure derivatives dC d trim variable computed by the program of a trim variable on the rigid aircraft is replaced by those imported by the TRIMINP bulk data card Once these pressure derivatives are replaced the aerodynamic stability derivatives of the trim variable are recomputed accordingly in the trim analysis Al INPCFDI A2 and INPCFD2 jointly construct the pressure derivatives of a trim variable For instance if the first set of pressure coefficients is at angle of attack 1 0 degrees and the second set pressure coefficients at angle of attack 1 5 degrees the pressure derivatives of the trim variable ALPHA See description of the TRIMVAR bulk data card are computed as INPCFD2 INPCFDI dC d ALPHA pat 1 5 1 0 2 0 INPCFD2 INPCFDI where INPCFD1 and INPCFD2 represent the first and second sets of the imported pressure coefficients Therefore Al 2 0 and A2 2 0 For the trim variable THKCAM INPCFD2 can be blank so that the mean flow pressure coefficients those imported by INPCFD1 with Al 1 0 It should be noted that the unit of the pressure derivatives is in 1 0 degree for ALPHA BETA and all control surfa
264. hord length Integer gt 0 THIRD is the identification number of an AEFACT bulk data card used to specify the camber of the airfoil in percentage of the chord length FOURTH and FIFTH are not used Integer gt 0 Remarks 1 The FOILSEC bulk data is referred to by a PAFOILS bulk data card to define an NACA series type of airfoil section 2 The resulting airfoil shape is the superposition of all airfoil sections multiplied by COEFF Thus the resulting airfoil shape is F x M COEFF x f x i l where F x is the resulting airfoil shape as a function of the chord x and is the ith airfoil section 4 02 BULK DATA DESCRIPTION GENBASE GENBASE Generates an Aerodynamic Database Description Generates an aerodynamic database by referring to a number of AEROGEN bulk data cards Format and Example 1 2 3 4 5 6 7 8 9 10 GENBASE IDBASE AEROFILE GEOFILE HEAT CONT CONT IDAERO IDAERO5 etc E GENBASE 100 AEROBASE DAT GEOFILE DAT AHEAT CONT CONT 1 3 4 131 5 7 9 EF Field Contents IDBASE Unique identification number referred to by a GENBASE Case Control Command Integer gt 0 See Remark 1 AEROFILE Character string up to 16 characters to specify a file name on which the aerodynamic database is to be exported Character See Remark 2 GEOFILE Character string up to 16 characters to specify a file
265. ian Little endian Big endian f T5 Without With Without With Without With Without With IBLANK IBLANK IBLANK IBLANK IBLANK IBLANK IBLANK IBLANK 1 0 BP3D IBP3D BP3DB IBP3DB BDP3D IBDP3D BDP3DB IBDP3DB or or or or or or or or a 1 0 BP3DI IBP3DI BP3DBI IBP3DBI BDP3DI IBDP3DI BDP3DBI IBDP3DBI p 1 0 10 BP3D2 IBP3D2 BP3DB2 IBP3DB2 BDP3D2 IBDP3D2 BDP3DB2 IBDP3DB2 1 0 y 10 BP3D3 IBP3D3 BP3DB3 IBP3DB3 BDP3D3 IBDP3D3 BDP3DB3 IBDP3DB3 Formatted Unformatted or Binary indicates that the CFD files are in ASCII format unformatted or binary respectively Solution normalized indicates that the CFD solution can be normalized using three options where is the freestream density is the freestream speed of sound P freestream pressure and is the freestream velocity Without IBLANK or with IBLANK indicates that the CFD mesh file is with or without IBLANK array respectively Single precision or Double precision indicates that the CFD files are generated by single precision computation or double precision computation respectively Little endian or Big endian see Remark 4 Little endian and big endian are different types of data formats adopted by computer platforms On Windows machines or other little endian systems CFD mesh and solution files created by big endian machines such as SGI and HP can be used with proper setting of FORMCFD to h
266. ication number of a PCHFILE bulk data card that imports a NASTRAN punch output file containing the symmetric and anti symmetric modal values of element forces stresses or strains respectively The trim results of all structural parameters listed in the ELLST and FIELD entries of the PCHFILE bulk data card are printed out Note that for output the LABEL and ISSET entries of the TRIMFNC bulk data card are replaced by the LABEL and ELLST entries of the PCHFILE bulk data card respectively Character string to specify whether the trim function is evaluated on the right hand side RHS or the left hand side LHS of the configuration Character See Remark 4 Two options are available RHS RHS on the right side of the configuration RHS LHS on the left hand side of the configuration ISSET is active only if the trim system is asymmetric or symmetric Integer or Character ISSET is used only for 1 TYPE AERO and LABEL TRIMVAR or LOADMOD 2 TYPE FEM and LABEL LOADMOD or 3 TYPE MODAL 1 TYPE AERO LABEL TRIMVAR ISSET is an integer that is the identification number of TRIMVAR bulk data card listed in the TRIM bulk data card LABEL LOADMOD ISSET is an integer that is the identification number of a LOADMOD bulk data card 2 FEM LABEL LOADMOD ISSET is an integer that is the identification number of a LOADMOD bu
267. ication numbers of the surface grid points These grid points are located behind the root of the thick wing component where the wake from the wing root is attached Integer 0 Note that RWAKE also can be a character string AUTO that triggers the program to automatically search for the surface grid points located behind the root of the thick wing component Character AUTO See Remark 6 A CANT angle in degrees to adjust the grid points at the wing body junction CANTR is active only if ATTR YES Real Default 0 0 See Remark 7 X Y and Z location of the tip chord leading edge Real Length of the tip chord Real Same as ATTR but for the tip of the thick wing component Character Same as LRCHD but for the tip of the thick wing component Integer 0 Same as RWAKE but for the tip of the thick wing component Integer 0 BULK DATA DESCRIPTION 4 175 THKWING CANTT Same as CANTR but for the tip section Real Remarks 1 The THKWING bulk data card automatically generates a set of surface grid points COUADA CTRIA3 elements on the upper and lower surface of the thick wing components In addition a set of CBAR elements are also automatically generated along the upper and lower surfaces of the trailing edge grid points Note that the input entries of the THKWING bulk data card are very similar to those of the CAERO7 bulk data card However the THKWING bulk data card generates a thick wing componen
268. icient size to accommodate all jobs submitted under the ZONAIR script file There is no rule of thumb for how large this space should be since the capability of ZONAIR in terms of the size of the input model is only limited by the memory and disk space of the hardware 2 4 OUTPUT FILES Output File A minimum of two output files are generated for a given ZONAIR job The first output file contains the standard output from ZONAIR program The name of the output file will either be the name provided to the ZONAIR script file or will be the input filename with an extension of out For example zonair testcase inp would generate an output filename of testcase out while 2 4 How TO RUN ZONAIR zonair testcase inp jobl txt would generate an output filename of job1 txt The output file contains information such as sorted bulk data input interpolated modes on aerodynamic boxes steady pressure results stability derivatives etc Logfile The second output file is a logfile that contains the run times of the ZONAIR engineering module calls A sample of this output is shown in Figure 2 3 The logfile provides the elapsed time Central Processing Unit CPU time and step CPU time for all module calls made during execution of ZONAIR The logfile name will always be the input filename with an extension of 1log For example zonair testcase inp jobl txt would generate a logfile filename of testcase 1og The logfil
269. ickness distributions are computed by linear interpolation from the wing root to the wing tip BULK DATA DESCRIPTION 4 131 8 8 Airfoil Section Property Description Defines an NACA series type of airfoil section at the root and tip of a wing like aerodynamic component referenced by the CAERO7 bulk data card Note that the PAFOILS bulk data card is an alternative form of the PAFOIL7 bulk data card except for defining an NACA series type of airfoil section Format and Example 1 2 3 4 5 6 7 8 9 10 PAFOIL8 IROOT ITIP PRINT INTERP REVERSE umma ves Field Contents ID Identification number that is referred to by a CAERO bulk data card Integer gt 0 See Remark 1 RADR Leading edge radius at the root normalized by the root chord in percentage of the chord length Real 2 0 0 IROOT Identification number of an FOILSEC bulk data card to define the airfoil section at root chord Integer gt 0 RADT Same as RADR except for the tip chord Real 2 0 0 Same as except for the tip chord Integer gt 0 PRINT Flag for printing out the airfoil shape on the standard output file PRINT 1 for printing Integer INTERP Character string either LINEAR or CUBIC For INTERP LINEAR use linear interpolation to interpolate the airfoil thickness distribution to the CAERO7 macroelement Otherwise cubic spline is used Character Default CUBIC R
270. if aa XZS YM YES on the AEROZ bulk data card E CL n UE E E Figure 5 2 Half Model for Symmetric Configuration The flight condition of the configuration is specified in terms of the freesteam Mach number M the angle of attack a side slip angle roll rate p pitch rate q and yaw rate The definition of these parameters is shown in Figure 5 3 5 2 GUIDELINES FOR AERODYNAMIC MODELING Figure 5 3 Definition of a P p 4 and y The Mach number is specified by a MACH bulk data card and f p 4 and y are specified by AEROGEN bulk data card Other parameters involved in the flight condition definition are the control surface deflection structural deformation due to smart structural actuation and jet force which can be specified by the AESURFZ PZTMODE and JETFRC bulk data cards respectively 5 2 SURFACE DISCRETIZATION BY GRID POINTS AND PANELS A ZONAIR aerodynamic panel method is normally constructed by first discretizing the configuration surface into many grid points the GRID bulk data cards and then connecting those grid points with either quadrilateral panels the CQUAD4 bulk data cards or triangular panels the CTRIA3 bulk data cards ZONAIR distributes an unknown constant source singularity on each panel and an unknown doublet singularity at each grid point In addition these doublet singularities are further linearly distributed over
271. ij Yij GCOL GROW CROW CONT 05 Field Contents Character string to define the name of the matrix Character See Remark 1 The precision of the matrix Any one of the following character string RSP RDP CSP or CDP Character See Remark 2 Character string either REC or SYM Character See Remark 3 Identification number of a grid point in the structural finite element model for column index Integer gt 0 See Remark 4 Component number for GCOL 1 lt CCOL lt 6 Integer gt 0 Identification number of a grid point in the structural finite element model for row index Integer gt 0 See Remark 5 Component number for GROW 1 lt CROW lt 6 Integer gt 0 Matrix terms xj is real part for real or complex matrix is the imaginary part for complex matrix is not used for real matrix Noted that x and occupy 2 fields for each input value Real See Remark 6 4 78 BULK DATA DESCRIPTION DMIG Remarks 1 DMIQG creates a matrix with entity name NAME The size of matrix is g set by g set where g set is 6 number of structural grid points This matrix can be used to specify an elementary mass or stiffness matrix of an element in the structural finite element model as a design variable for sensitivity analysis 2 RSP Real Single Precision RDP Real Double Precision CSP Complex Single Precision and CDP Complex Double Precision 3 REC Rectangular mat
272. in file DIRNAME FIX located in the ZONAIR home directory 6 Establish a run time database folder i e directory using the current process id as an extension For example 7 1 0001 7 the complete pathname pathname specified in DIRNAME FIX along with the current run time database folder name to file DIRNAME TMP This temporary file is read by the ZONAIR software system to know where the database files of the current job are to be executed 8 Execute the ZONAIR software system using the input output filenames 9 the logfile from the run time database folder to the local directory 10 Delete the database folder and scratch files 11 Notify user of job termination by a beep sound Windows DOS Multiple jobs can be submitted in the PC environment submitting multiple jobs is optional not a requirement The exception to this case would be if the host system is operating under MS DOS and does not utilize the Windows operating system Win 95 98 NT In this situation only one job can be submitted at a time which will tie up the machine until the job terminates unless the user can utilize multiple command interpreters with the option to toggle between them For a system with Windows installed multiple jobs can be submitted by opening up multiple MS DOS command prompt windows and submitting one job per Window For example to submit two jobs in Windows 95 98 NT called testi inp and test2 inp perform the fol
273. ine module As an example of such a scenario Figure 6 1 shows the cross section of a wing like component in which the solid circles represent the finite element grid points on the upper and the lower skins and the line represents the side view of a macroelement finite element grid points appear to be well separated If the IPS method is selected as the spline method the spline module projects the finite element grid points onto the plane of the macroelement Figure 6 1 b This plane is called the spline plane Structural Finite Element Grid Points Projection onto the CAERO7 Plane EE res Tm e i i i i e eee Side View of CAERO7 a b Figure 6 1 Cross Section of a Wing Like Component If the projection of two grid points on the spline plane are too close to one another an ill conditioned spline matrix results In this situation the error condition may not be detected by the spline module To avoid this input error it is recommended that either the upper or the lower grid points but not both be included in the SET1 bulk data card The spline case illustrated in Figure 6 1 a is an ideal case for the TPS method Since TPS is a 3 D spline method there is no requirement to define a spline plane for grid point projection Therefore all upper and lower grid points can be included in the spline However this is true only for a thick wing like component As de
274. ines the vortex cores are connected by a CROD element and the vorticity feeding points are connected by a set of CSHEAR elements These CSHEAR and CROD elements and their connectivities are automatically generated by the program 2 In order to introduce vorticity due to the potential difference between the upper and lower wing surfaces and to feed this vorticity into the vortex roll up line the user must first separate the surface grid points along the wing side edge into two sets of grid points except the first surface grid point at the leading edge where the vortex core starts One set of grid points is along the upper surface and the other along the lower surface In the following figure the leading edge of the 70 degree delta wing is separated by two sets of three surface grid points except the first surface grid point 4 206 DATA DESCRIPTION VORNET GRIDU Y GRIDL This first surface grid point is specified in the entry TIPGRID The entire vortex roll up model should consist of three regions the vortex roll up sheet from the wing leading edge to the trailing edge the vortex roll up sheet in the wake region and the wake sheet behind the wing trailing edge The number of vortex roll up lines in the first region 1s defined by entry NTIP and in the wake region is defined by entry NWAKE The wake sheet behind the wing trailing edge can be specified using the WAKENET bulk data card An example of the wake sheet behind the wi
275. inning of the input file Its major functions are e to define the filename that contains the free vibration output from the structural finite element methods for static aeroelastic analysis e allow direct matrix input e turn on diagnostic routines The Case Control Section must be located after the Executive Control Section and before the Bulk Data Section Its major functions are e input title cards that describe the ZONAIR analysis e select the disciplines aerodynamic analysis aeroheating analysis trim analysis etc for the analysis A typical example of the Executive Control and Case Control Sections is shown as follows Begin Executive Control Section ASSIGN FEM demol f06 FORM MSC BOUND SYM PRINT 1 ASSIGN FEM demo2 f06 FORM MSC BOUND ANTI ASSIGN MATRIX demol mgh MNAME AMGH ASSIGN MATRIX demol kgh MNAME AKGH SOL 1 DIAG 1 3 CEND Begin Case Control Section TITLE DEMO WING BODY CASE ECHO SORT SUBCASE 1 SUBTITLE Aerodynamic Analysis ABEL at Mach 0 8 AEROGEN 10 SUBCASE 2 UBTITLE Aeroheating Analysis ABEL at Mach 0 8 THERMAL 20 SUBCASE 3 SUBTITLE Trim Analysis ABEL at Mach 1 2 TRIM 30 BEGIN BULK Begin Bulk Data Section EXECUTIVE CONTROL AND CASE CONTROL SECTIONS 3 1 3 1 EXECUTIVE CONTROL SECTION The Executive Control Section allows the following Executive Contr
276. ins a matrix in the OUTPUTA format See the description of the OUTPUTA format This matrix has 8 columns and n rows where n is the number of surface panels and the 8 columns are Column 1 Perturbation U velocity on the right hand side of the aerodynamic model Column 2 Perturbation V velocity on the right hand side of the aerodynamic model Column 3 Perturbation W velocity on the right hand side of the aerodynamic model Column 4 Cp on the right hand side of the aerodynamic model Column 5 Perturbation U velocity on the right left side of the aerodynamic model Column 6 Perturbation V velocity on the right left side of the aerodynamic model Column 7 Perturbation W velocity on the right left side of the aerodynamic model Column 8 Cp on the left hand side of the aerodynamic model Note first 8 characters are the character specified by the HEAT entry and the last 4 characters contain an integer starts from 0001 to 000n where n is the total number of AEROGEN bulk data cards referred to by the IDAERO entry The value of those parameters in Card 5 13E12 4 A12 Note that these values are specified by the AEROGEN bulk data cards Thus the number of card 6 is the number of AEROGEN bulk data cards that are referred to by the IDAERO entry 3 panel data is stored in the following format Card 1 NPANEL NGRID Format NPANEL Number of panels Integer gt 0 NGRID Number of grid points Integer
277. ion of the z axis The third point defines a vector which with the z axis defines the x z plane The reference coordinate system must be independently defined Format and Example 1 2 3 4 5 6 7 8 9 10 CORD2R CID RID A1 A2 A3 B1 B2 B3 CONT CONT gi C2 c3 CORD2R 3 17 2 9 1 0 0 0 3 6 0 0 1 0 423 23 5 2 1 0 2 9 Field Contents CID Coordinate system identification number Integer gt 0 RID Reference to a coordinate system which is defined independently of new coordinate system Integer 0 or Blank Ai Bi Ci Coordinates of three points in coordinate system defined by RID Real Remarks 1 A continuation entry must be present 2 The three points 2 A3 B2 B3 C2 C3 must be unique and noncollinear Noncollinearity 1s checked by the geometry processor 3 Coordinate system identification numbers on all CORDIR CORDIC CORDIS CORD2R CORD2C and CORD2S entries must all be unique 4 An RID of zero references the basic coordinate system 4 62 DATA DESCRIPTION CORD2R 5 location of a grid point P in the sketch in this coordinate system is given by X Y Z 6 The displacement coordinate directions at P are dependent on the location of P as shown above by ux uy uz BULK DATA DESCRIPTION 4 63 CORD2S CORD2S Spherical Coordinate System Definition Form 2 Description Defines a spherical coor
278. ion on the aerodynamic model Every streamline starts from the stagnation point and ends at the control point of the aerodynamic panel These streamlines are computed based on the inviscid surface velocities generated by the AEROGEN bulk data card The aeroheating results are calculated along each streamline using a one dimensional boundary layer method The aeroheating results stored on file FILENM include The aerodynamic panel model with both upper and lower surfaces of the CAERO7 macroelements being modeled The pressure coefficients the friction coefficients the heat transfer coefficients the wall enthalpy the wall temperatures the heat flux the wall pressure and the flow laminar transition turbulent regime at the aerodynamic grid points The streamlines for the stagnation point to the control points of the aerodynamic panels Include only if STREAM z 0 PATRAN requires that the aerodynamic model be stored in a neutral file and that analysis results be stored in a results file Therefore the AEROGM entry is used to assign a name for a neutral file that contains the aerodynamic model while the FILENM entry specifies a file that will contain the aeroheating results BULK DATA DESCRIPTION 4 173 THKWING THKWING Aerodynamic Thick Wing Component Description Defines an aerodynamic wing macroelement of a thick wing component Format and Example THKWING Ie PSHELL ACOORD NSPAN NCHORD PAFOIL7 AUTOTIP
279. ion solutions Since ELFINI always outputs the free vibration solutions in SI Standard International format metric Length meters Mass kilograms the structural model and aerodynamic model may be in different unit systems for this option only Again different units between the structural and aerodynamic models is only allowed for this type of input FORM ELFINI To convert the ELFINI metric units to the aerodynamic model units requires specifying the FMMUNIT and FMLUNIT entries of the AEROZ bulk data card to reflect the units of the aerodynamic The program will then convert the ELFINI free vibration solutions to match the units of the aerodynamic model If the aerodynamic model is also in SI units then the FMMUNIT and FMLUNIT entries model should be set to KG and M respectively 54930 03 0 00000E 0010202 01833E 02 0 00000E 0010203 04441 02 0 00000E 0010204 19419 02 0 00000E 0010301 77315E 03 0 00000E 0010302 03253E 02 0 00000E 0010303 17388E 02 0 00000E 0010304 14665 02 0 00000E 0010401 08321E 02 0 00000E 0010402 16488 02 0 00000E 0010403 13555E 02 0 00000 00 10404 19065 02 0 00000E 00 20000 00000 00 0 00000E 00 A sample of the ELFINI neutral file is shown as follows HEADER MODEL RELEASE I NAME E767 DATE 30 10 96 AT 10 49 10 TITLE NO TITLE END TITLE END HEADER CONTENT DEGREE NBDOF 30 K MATRIX NBMATRIX iE M MATRIX MONVAL END CONTENT NBMATRIX
280. is coordinates This normally gives a non diagonal generalized mass matrix that in fact contains the physical mass properties of the structure Note that if only one half of the configuration is modeled XZSYM YES in the AEROZ bulk data card these mass properties are only one half of the mass and mass moment of inertia of the whole configuration Note that to compute the distributed inertial loads of a free free structure for trim analysis requires activating the SUPORT entry Otherwise the program assumes that the structure is restrained and ignores the distributed inertial load effects EXECUTIVE CONTROL SECTION 3 19 ASSIGN MATRIX ASSIGN MATRIX Direct Matrix Input by INPUTT4 Format Description Assign an external file that contains the ASCII or binary data of a matrix for direct matrix input The format of the external file is the same as the INPUTT4 format of NASTRAN see INPUTT4 or OUTPUT4 module description of MSC NASTRAN DMAP Module Dictionary Format ASSIGN MATRIX a FORM b MNAME c PRINT Example 1 ASSIGN MATRIX demol mgh MNAME SMGH FORM FORMAT PRINT 1 Example 2 ASSIGN MATRIX export home ZONAIR demo2 mgh FORM UNFORMAT Describer Meaning MATRIX a MATRIX indicates that a is the filename of the external file that contains the data of a matrix for direct matrix input represents a character string specifying the name of the external file Re
281. is automatically generated RBE2 is set to be It should be noted that for the example shown in the figure above two SLICE bulk data cards are required SLICE 201 101 103 NO 200 NO SLICE 205 103 106 YES 0 The first SLICE bulk data card slices the edges between the grid points 101 and 103 as well as 101 and 200 and automatically generates grid points 201 202 203 and 204 where 201 and 202 are attached to the panels along the trailing edge on the lower surface and 203 and 204 are attached to the panels along the tip on the lower surface The second SLICE bulk data card slices the edges between the grid points 103 and 106 and generates grid points 205 206 207 and 208 A RBE2 element is also internally generated with 4 162 DATA DESCRIPTION SLICE entries GRIDU 106 GRIDL 208 and GRID1 AUTO Note that there is no slicing action along the wing tip by the second SLICE bulk data card because ENDRG 0 If the grid point ENDRG is located at the leading edge of the wing tip SPLIT must be NO This is because the two sets of line vortex along the upper and lower surfaces of the wing tip are originated from the leading edge thereby they must share the same grid point ENDRG BULK DATA DESCRIPTION 4 163 SPLINEO SPLINEO Zero Displacement of Aerodynamic Panels Description Imposes a zero displacement condition on aerodynamic panels SPLINEO bulk data ca
282. isplacement spline matrix and UGFRC is the force spline matrix If there is no SPLINEF bulk data card specified then JUGFRC UGTKG 2 spline module first generates the UGTKG matrix by processing all ATTACH SPLINEO SPLINEI SPLINE2 and SPLINE3 bulk data cards Then the spline module processes the SPLINEF bulk data cards to alter the SPLINE1 SPLINE2 or SPLINE3 bulk data cards by a new set of structural grid points involved in the force spline The new set of spline bulk data cards along with all of the rest of the unaltered spline bulk data cards not referred to by the SPLINEF bulk data card are used to generate the UGFRC matrix 3 ensure a continuous displacement and slopes at the aerodynamic grid points by the displacement spline matrix the generation of UGTKG matrix may need more structural grid points However to achieve a good force spline it is recommended to select less structural grid points involved in the UGFRC matrix 4 168 DATA DESCRIPTION SPLINEF This is because one aerodynamic box produces only one aerodynamic force If there are more than one structural grid points located on one aerodynamic box the UGFRC matrix needs to split one aerodynamic force at more than on structural grid points This may result in an irregular distribution of the force distribution at the structural grid points Note that based on the principle of virtual work the conservation of the total force is ensured
283. it is referred to by TRIMINP bulk data card Integer See Remark 1 TRANSF Identification number of a CORD2R bulk data card defining a coordinate system in which the CFD mesh is located Note that TRANSF can be a negative integer This negative sign implies that the CFD mesh is located in the negative Y axis Integer Default 0 See Remark 2 DATA Character string to specify the type of result stored on the external file CFDFILE Character For DATA PLOT3D the CFD results in terms of RHO RHOU RHOV RHOW and E where RHO is the density RHOU RHOV and RHOW are the non dimensional momentum along x y z respectively and E is the energy For DATA PLOT3D the CFD results are in terms of RHO U V W Cp Po M and 5 where V W are the non dimensional velocity components normalized by the freestream velocity C is the pressure coefficients P is the non dimensional pressure M is the local Mach number and S is the entropy For definitions of these non PLOT3D variables See Remark 6 CFDFILE Character string to specify the file name that contains the unstructured CFD mesh and solution If the first character starts with a dollar sign the rest of the characters must be integers This integer 1s the identification number of an EXTFILE bulk data card where the filename is specified This feature allows for filenames up to 72 characters to be input Character See Remark 3 BULKDATA DESCRIPTION 4 10
284. ix 4 042 001 0 0 0 01 5 0 0 01 7 04 7 0i 0 0 0 01 0 0 0 01 6 0 6 01 4 04 4 01 QQQ 6 DMIS can be repeatedly specified for each column of the matrix For columns that are not referred to by the DMIS bulk data card null columns are assumed BULK DATA DESCRIPTION 4 83 EXTFILE EXTFILE External File Description Defines a character string as the name of an external file Format and Example i 2 3 4 5 6 7 8 9 10 EXTFILE 100 ZAERO TestCases flutter casel ext dat Field Contents ID Unique identification number Integer gt 0 See Remark 1 FILENM This feature allows for filenames up to 72 characters with no embedded blanks to be input Note that unlike all other bulk data cards where any characters are converted to upper case these characters will not be converted to upper case This feature is important for the UNIX system because it is case sensitive Remarks 1 The EXTFILE bulk data card is referred to by other bulk data cards that require external file for input or output Whenever an external file name 1s needed in a bulk data card for input or output rather than directly specifying a character string for the file name the user can specify a character string started with a dollar sign and followed by an integer for instance 101 This integer is used to refer to the identification number of the EXTFILE bulk data card where the actual file name is specified by FILENM
285. ix AMGH must be imported by the ASSIGN MATRIX Executive Control 4 188 DATA DESCRIPTION TRIMFNC Command with MNAME AMGH For asymmetric trim system trim degrees of freedom involve both symmetric and anti symmetric trim systems both SMGH and AMGH matrices must be imported It should be noted that if the computation of inertial loads is invoked the SUPORT entry in the ASSIGN FEM Executive Control Command must be specified to define the degrees of freedom of the rigid body modes of the structural finite element model Note The sign of the component loads is defined in the structural finite element basic coordinate that is specified by the ACSID entry of the AEROZ bulk data card Since the ZONAIR static aeroelastic trim analysis employs the modal approach to solve the trim system of the flexible aircraft any structural quantities such as element stresses forces displacements etc can be obtained by the superposition of their respective modal data of each mode These modal data must be imported from the structural finite element analysis For instance to obtain the modal data of stress by NASTRAN the user can use the NASTRAN Case Control Command such as STRESS ALL in the NASTRAN free vibration analysis The user can select the modal stresses of a particular element or a group of element of interest and import these data to ZONAIR by the AEFACT bulk data card for one element DMI bulk data card or ASSIGN
286. l FIRST the design lift coefficient FIRST 3 20 SECOND the twice the location of maximum camber in tenths of chord SECOND 20 THIRD 0 1 a reflexed trailing edge FOURTH the airfoil thickness in percent chord FIFTH the first and second digit of the appended number the first digit 0 3 6 or 9 which indicates leading edge radius index number the second digit indicates the location of maximum thickness in tenths of chord Example NACA 24012 34 PROFILE 16 NACA 16 series airfoil FIRST the design lift coefficient in tenths SECOND the airfoil thickness in percent chord THIRD FOURTH and FIFTH are not used Example NACA 16 212 PROFILE 63 6 64 64 65 65 66 and 67 NACA 6 series airfoil FIRST the design lift coefficient in tenths SECOND the airfoil thickness in percent chord THIRD FOURTH and FIFTH are not used Example NACA 63 412 654 310 BULK DATA DESCRIPTION 4 91 FOILSEC For TYPE USER FIRST is the identification number of an AEFACT bulk data card used to specify the x coordinate locations in percentage of the chord length where the thickness and camber are specified The first value listed in the AEFACT bulk data card must be 0 0 an the last value must be 100 0 SECOND is the identification number of AEFACT bulk data card used to specify the half thickness of the airfoil in percentage of the c
287. l Symmetric modal matrix computed SPHIK SPHIK a uGTKG SPH Kset x Hset Real APHIK Same as SPHIK but for the anti symmetric modes Kset x Hset Real Symmetric modal mass SMGH MGH Mes SPHI Gset x Hset Real Where M gg is the G set mass matrix AMGH Same as SMGH but for the anti symmetric mode Gset Hset Real Kset x NCS where NCS is the Symmetric control surface modes at aerodynamic number of RENTER panels AESURFZ bulk Real data cards with entry SYM Kset x NCA where NCA is the number of ACNTLK Anti symmetric control surface modes at aerodynamic AESURFZ bulk Real panels data cards with entry ANTISYM SCNTLG Same as ACNTLK but at structural grid Gset x NCS Real ACNTLG Same as ACNTLK but at structural grid Gset x NCA Real Integration matrix converts C p t0 forces F on SKJ Jset x Kset Real aerodynamic panels F SKJ f p 3 The OUTPUTA format is always non sparse format BULK DATA DESCRIPTION 4 129 PAFOIL7 PAFOIL7 Airfoil Section Property Description Defines the airfoil cross sections at the root and tip of a wing like aerodynamic component referenced by the CAERO7 and THKWING bulk data cards Format and Example 1 2 3 4 5 6 7 8 9 10 Field ID ITAX ITHR ICAMR RADR ITHT ICAMT RADT Remarks Contents PAFOITL identification number Integer gt 0 Identification number of an AEFACT bulk
288. l because point B should be identified as the lower side panel Instead of point B if point is used the separation process may work because A is located on the upper side of the CAERO7 and is on the lower side The point B is calculated by moving point B with a large negative ZOFF value so that it is located in the lower side of the CAERO7 macroelement Two CQUAD4 Panels Tr B ZOFF CAERO7 Bec Another case where the separation process may fail is a sharp turn occurred in the search vectors involved in the SLICE RBE2 bulk data card In the following figure this sharp turn occurs at point B between the vectors B and B C For the CTRIA3 with three corner grid points BCD its centroid is located on the upper side of vector A B but becomes the lower side of vector B C This is a fatal error because this CTRIA3 should be on both of the lower sides of vectors A B and B C This fatal error can be removed by introducing a large negative ZOFF for this so that its centroid 1s moved from E to Now because is located on the lower side of vector A B and B C the separation process can identify this CTRIA3 as the lower side panel 4 152 DATA DESCRIPTION PSHELL Lower BULK DATA DESCRIPTION 4 153 PZTMODE PZTMODE Control Force Due to Smart Structural Actuation Description Defines a control force generated by the structural deformati
289. lacement at a structural finite element grid point 1s defined as the trim function The grid point identification number is specified the ISSET entry and the component number is specified in the IASET entry see Remark 2 FORCE The force at a structural finite element grid point is defined as the trim function The grid point identification number is specified the ISSET entry and the component number is specified in the IASET entry For TYPE MODAL The resultant value from the superposition of the modal data of the flexible aircraft is defined as a trim function LABEL must be either AEFACT or DMI 4 186 DATA DESCRIPTION TRIMFNC RHS ISSET Characters Description LABEL AEFACT The modal data is specified by the AEFACT bulk data card The identification number of the AEFACT bulk data card for the symmetric or asymmetric modal data is specified in the ISSET entry whereas the anti symmetric modal data in the IASET entry See Remark 3 LABEL DMI The modal data is imported either by the DMI bulk data card or the ASSIGN MATRIX Executive Control Command The name of the matrix that contains the symmetric or asymmetric modal data is specified in the ISSET entry whereas the anti symmetric modal data in the IASET entry See Remark 3 LABEL PCHFILE For the structural parameters defined by a PCHFILE bulk data card ISSET and IASET are the identif
290. lank that defines a matrix operation for the matrix MATRIXA Character Default Blank See Remark 3 where INV Invert COEFFA MATRIXA TRNS Transposed COEFFA MATRIXA PRINT Print out the matrix RESULT GTOA Reduce rows and columns of MATRIXA from g set to a set ATOG Expand rows and columns of MATRIXA from a set to g set The elements in the expanded submatrices are zero COLGTOA Reduce the columns of MATRIXA from g set to a set COLATOG Expand the columns of MATRIXA from a set to g set ROWGTOA Reduce the rows of MATRIXA from g set to a set ROWATOG Expand the rows of MATRIXA from a set to g set Note g set is 6x number of structural grid points of the FEM model a set is 6x number of structural grid points defined by DISP n NASTRAN Executive Control Command or the grid point defined by the FEMASET bulk data card See ASSIGN FEM Executive Control Command for the description of g set and a set COEFFA real multiplication factor for matrix MATRIXA Real Default 1 0 BULK DATA DESCRIPTION 4 29 ALTER MATRIXA Character string that is the name of the matrix MATRIXA Character See Remark 4 SYMBOL Character string either 4 4 or blank where p represents addition represents subtraction represents multiplication fp represents appending Character
291. le i 2 3 4 5 6 7 8 9 10 wer uer LE d T Dd DMIG1 DMIG2 QUAD2 DMIG3 DMIG4 Field Contents IDSEN Unique identification number Integer gt 0 See Remark 1 IDFLT Identification number of a TRIM Case Control Command of which the sensitivities of a response will be computed Integer gt 0 See Remark 2 FILENM Character string to specify a file name on which the sensitivities of the forces at structural grid points are stored If the first character starts with a dollar sign the rest of the characters must be integers This integer 1s the identification number of an EXTFILE bulk data card where the filename is specified This feature allows for filenames up to 72 characters to be input Character or Blank LABEL Any character string to define the name of the design variable LABEL is used only for identifying the design variable in the output Character THICKi THICKi could represent the thickness of a membrane element the area of a rod element or area moment of inertia of a beam element Real gt 0 0 See Remark 3 MASSi Character string that matches the entry NAME of a DMIG DMI bulk data card or MNAME of ASSIGN MATRIX Executive Control Command This matrix is used as the elementary mass matrix of the design variable with value of THICK Character STIFFi Character string that matches the entry NAME of a DMI
292. le Therefore the AERONM entry is used to assign a name for a neutral file that contains the aerodynamic model while the FILENM entry specifies a file that will contain the displacement results For more details please see section 7 5 PATRAN Compatible Output 4 146 DATA DESCRIPTION PLTTRIM PLTTRIM Generation of an ASCII Text File for the Post Processing of the Static Aeroelastic Trim Analysis Description Defines the name of a data file in which the aerodynamic pressure distribution deformed aerodynamic model or flight loads generated by the static aeroelastic trim analysis are stored Format and Example Field Contents IDPLT Identification number Integer gt 0 See Remark 1 IDTRIM Identification number of a TRIM bulk data card Integer gt 0 See Remark 2 FLEX Character String either FLEX or RIGID Character Default FLEX FLEX FLEX for the results of the flexible aircraft FLEX RIGID for the results of the rigid aircraft TYPE Character string Character TYPE FORCE Stores the flight loads in terms of NASTRAN FORCE and MOMENT bulk data cards at the structural finite element grid point on the ASCII file The user can insert this file into the NASTRAN model for detailed stress analysis by performing a static structural analysis TYPE CP Stores the distributed aerodynamic pressure distribution of the aerodynamic model on the file for graphic display
293. lk data card LABEL GRIDDISP ISSET is an integer that is the identification LABEL FORCE number of a structural finite element grid point BULK DATA DESCRIPTION 4 187 3 MODAL LABEL LABEL DMI LABEL PCHFILE ISSET is an integer that is the identification number of the AEFACT bulk data card containing the modal data associated with the symmetric modes The number of data must be the same as the number of the symmetric modes Used only for symmetric or asymmetric trim system ISSET is a character string that is the name of the matrix imported either by the DMI bulk data card or ASSIGN MATRIX Executive Control Command The modal data contained in the matrix is associated with symmetric modes The number of rows of the matrix must be the same as the symmetric modes Used only for symmetric or asymmetric trim system ISSET is an integer that is the identification number of a PCHFILE bulk data card to specify the symmetric or asymmetric modal data IASET IASET is active only for anti symmetric or asymmetric trim system 1 TYPE MODAL LABEL AEFACT LABEL DMI LABEL PCHFILE 2 TYPE FEM IASET is an integer that is the identification number of the AEFACT bulk data card containing the modal data associated with the anti symmetric modes The number of modal data must be the same as the number of anti sy
294. locked token s re starting the ZLS will also free up locked token s However doing this will also release the token s that might be checked out by other job s and all on going job s will terminate due to ZLS restart Therefore it is strongly recommended to check if there is any job running before re starting the ZLS by either 1 Clicking on the List Current Jobs button within the ZONA License Monitor Windows program see Section 6 1 of the ZLS User s Manual or 2 Executing a java zls serverwhatsrunning from a prompt in an MS DOS or command window see Section 5 4 of the ZLS User s Manual Both 1 and 2 will show information related to any on going job executions If ZLS is re started for any reason including a reboot of the computer any remaining token files found in the ZLS log folder under the ZONAIR home directory can be deleted before any new ZONAIR job s submitted These old token files are no longer useful since the ZLS record is cleared upon the ZLS re start How TORUNZONAIR 2 11 2 7 6 HEARTBEAT During execution of ZONAIR heartbeat signals are continuously sent back and forth between ZONAIR and the ZLS Failure in receiving a heartbeat signal by a ZONAIR job will result in termination of that ZONAIR job To avoid such a termination the ZLS needs to be up and running all the times during the execution of ZONAIR job s and the network connection between the machines running ZONAIR and hosting the ZLS m
295. lowing 1 From the Start menu select Programs MS DOS Prompt Note The MS DOS window can be maximized or minimized Also Note Terminating an MS DOS window during execution of a job will terminate that ZONAIR job 2 Change the directory to where the input deck resides 3 Typein the following at the command prompt zonair testl inp and press the return key 4 second MS DOS window as described in step 1 above 5 Repeat step 2 from above 6 Typein the following at the command prompt 2 8 HowTo RUN ZONAIR zonair test2 inp and press the return key Two jobs will be submitted each with a unique folder designation e g ZONAIROOI and will be located in the run time database directory specified by the pathname in file DIRNAME FIX Multiple jobs can be submitted from either the same directory or different directories Associated output files will be placed in the directories from which the input jobs were submitted Any AIC files to be read in for a restart run process must also be located in the directory from which the input job is submitted At the end of each batch job process the script file will notify the user of job termination by a beep sound As a final note the input output decks are in ASCII text format and can be viewed and or modified with any editor on the host system such as the DOS editor initiated in a MS DOS Window by edit PC Script File Process This is identical to the
296. lowing figure the NYth wake line is at the tip of the thick wing component Therefore LINENY is recommended to model the tip vortex effects of the thick wing component In order to extend the wake surface to infinite LINETE CBAR is recommended so that additional flat wakes generated by the CBAR elements attached to the trailing edge of the curved wake surface BULK DATA DESCRIPTION 4 211 WAKENET Tip of the thick wing component CROD elements are added along the NY s wake line if LINENY CROD CBAR elements are added along the trailing edge if LINETE CBAR Flat wake generated by CBAR ea 5 The potential jump across the wake surface along the same wake line must be constant and equal to the potential difference between GRIDU and GRIDL In the following figure and represent the potential at the upper CSHEAR and lower CSHEAR respectively Program will impose the condition such that Peru bo e 9 Note that GRIDL GRIDL GRIDLyy 0 is allowed However GRIDL 0 and GRIDL Z 0 is not allowed In this case only one set of CSHEAR elements at the upper side of the wake surface is generated Also GRIDU is allowed This is used to model a curved wake surface shed from the surface grid behind the thick wing and body juncture where the entry GRID of the RBE2 bulk data card are
297. lts The correct technique for this spline case is to use the IPS method and to ensure that the inboard and outboard CAERO7 macroelements refer to all the grid points in the finite element model grid points 1 through 12 The infinite plates generated by the IPS method for these two macroelements are then identical leading to continuous displacements and slopes across these two wing components 6 4 MODELING GUIDELINES OF SPLINE FOR FLEXIBLE LOADS 6 4 ACCURATE ROTATIONAL STRUCTURAL DISPLACEMENT FOR BEAM SPLINE METHOD Unlike the IPS and TPS methods which adopt only the translational displacements at the structural grid points the beam spline method requires both the translational and rotational displacements Often in structural finite element analysis the translational displacements are included as the analysis set 1 e A set degrees of freedom Since the modal analyses of finite element methods only assure accurate modal displacements for the A set degrees of freedom exclusion of the rotational displacement for A set degrees of freedom in the beam spline method leads to inaccurate spline results on the aerodynamic model 6 5 INACCURATE SPLINE RESULTS DUE EXTRAPOLATION Since structural grid points are usually placed at major load carrying components the structural finite element model may appear to be shorter than the aerodynamic model A typical case where this can occur is in modeling the structural wing tor
298. lysis Among all AESURFZ AESLINK GRIDFRC PZTMODE and JETFRC bulk data cards LABEL must be unique BULK DATA DESCRIPTION 4 115 JOINTHK JOINTHK Join Two THKWINGs Description Joins two thick wing components that are generated by two THKWING bulk data cards Format and Example 1 2 3 4 5 6 7 8 9 10 JOINTHK LID THWNG1 RTL THWNG2 RT2 JOINTHK 100 1001 TIP 2001 ROOT Field Contents LID Identification number Integer gt 0 See Remark 1 THKWNGI Identification number of a THKWING bulk data card Integer gt 0 RTI Character either ROOT or For RTI ROOT The root section of the thick wing component is attached to another thick wing component defined by THK WNG2 TIP The tip section of the thick wing component is attached to another thick wing component defined by THK WNG2 THKWNG2 Same as THK WNGI but for the second thick wing component RT2 Same as RTI but for the THK WNG2 Remarks 1 The JOINTHK bulk data card internally generated a set of RBAR bulk data cards that merge the grid points along of THKWNG1 with those along RT2 of THKWNG2 Note that the chordwise divisions of THKWNGI and THK WNG2 must be the same Otherwise a fatal error occurs See the following figure as an example RT1 TIP Seine RT2 ROOT 4 116 BULK DATA DESCRIPTION LOADMOD LOADMOD Load Mo
299. m degrees of freedom approach in terms of the product of PHG and SMGH MGG PHG and the subscript s denotes that the matrix vector is for the symmetric structural modes Likewise for the anti symmetric trim system it can be shown that the matrix AMGH is computed by AMGH MGG PHG where PHG is the anti symmetric modal matrix 4 2 6 INPUT FOR PLOT FILE GENERATION ZONAIR does not provide graphic capability is the acceleration vector that is approximated by the modal Instead ZONAIR generates files that can be read by TECPLOT FEMAP PATRAN or I DEAS for post processing The bulk data cards shown in the following table can be specified to generate various output files Name Description Remarks PLTAERO Generates an ASCII text file for plotting the aerodynamic model Optional PLTCP Generates an ASCII text file for plotting the steady pressure Optional coefficients PLTMODE Generates an ASCII text file for plotting the interpolated structural Optional mode on the aerodynamic model PLTSURF ASCII text file generation for plotting the aerodynamic control Optional surface PLTTRIM Generates an ASCII text file for the post processing of the static Optional aeroelastic trim analysis BULK DATA DESCRIPTION 4 15 These bulk data cards are not referred to by other bulk data cards Their appearance in the Bulk Data Section triggers the program to generate th
300. m is used 3 structural grid points associated with the component should be included in the SET1 bulk data card Missing structural grid points that have attached mass can lead to incorrect inertial loads BULK DATA DESCRIPTION 4 117 MACH MACH Description Generates Aerodynamic Matrices At a Given Mach Number Generates Aerodynamic Influence Coefficient matrix at a given mach number Format and Example MACH Field IDMACH MACHNO METHOD RELAXW VISCOUS SAVE FILENM 1 2 3 4 5 6 7 8 9 IDMACH MACHNO METHOD RELAXW VISCOUS SAVE FILENM 10 Contents Identification number Integer gt 0 See Remark 1 Mach number Real gt 0 0 Flag for defining the aerodynamic method Integer METHOD 0 For subsonic and supersonic aerodynamics by solving the linear potential equation METHOD 1 For transonic aerodynamics METHOD 2 For hypersonic aerodynamics Identification number of a RELAXW bulk data card for wake relaxation Integer gt 0 or Blank See Remark 2 Identification number of a VISCOUS bulk data card to define the viscous parameters for skin friction computation and to introduce the viscous vortex model for the CROD elements Integer gt 0 See Remark 3 Save the Aerodynamic Influence Coefficient AIC matrices generated by the current MACH bulk data card to file FILENM or retrieve AIC from FILENM Characters or blank SAVE SAVE saves the AIC data SAVE
301. m the shape of the wake surface the flat wake surface is recommended for the modeling of the wake surface However for a closely coupled wing tail configuration Figure 5 8 a where the wake shape from the wing dominates the downwash effects on the tail a flat wake modeling apparently may give large discrepancy on the aerodynamics of the tail Furthermore for a coplanar wing tail configuration Figure 5 8 b because the flat wake surface from the wing can penetrate into the tail a singularity may occur which is obviously incorrect For these cases the curved wake modeling is recommended which is specified by the WAKENET bulk data card C 10 a Closely Coupled b Coplanar Wing Tail Wing Tail Configuration Configuration Figure 5 8 Cases Where the Flat Wake Surface is Not Recommended GUIDELINES FOR AERODYNAMIC MODELING 5 5 Figure 5 9 shows a curved wake surface that is modeled by NY wake lines and NX grid points along each wake line The locations of the NY x NX grid points are specified by the user if the shape of the wake surface is known ZONAIR constructs two sets of the CSHEAR panels between these grid points with one set of the CSHEAR panels is on the lower surface Similar to the flat wake surface a constant doublet singularity along the chordwise direction is distributed on each CSHEAR panel to satisfy the wake condition However since the wake shape is usually not known ZONAIR provides a wake relaxation techniqu
302. mber of FEM grid points could be time consuming The SPLINEM bulk data card can avoid the recomputation of the spline matrix if both the aerodynamic and the structural finite element grid points are unchanged 5 Because the spline matrix is independent of Mach number the spline matrix can be first saved in the cold start job and then retrieved for other Mach numbers in the restart job 4 170 DATA DESCRIPTION THERMAL THERMAL Aeroheating Analysis Description Performs the aeroheating analysis at a specified flight condition Format and Example THERMAL SETID IDAERO TEMP E HOTWALL sme IGAS EMIT CONT Field Contents SETID Identification Number Integer gt 0 See Remark 1 IDAERO If IDAERO 0 IDAERO is the identification number of an AEROGEN bulk data card that defines the flight condition for the aeroheating analysis If IDAERO 0 IDAERO is the identification number of a FLEXLD bulk data card to perform an aeroheating analysis with structural flexibility effects In this case SOL 1 and ASSIGN FEM executive control commands must be specified TEMP Initial surface temperature TEMP is a real number with a character F or C attached to the end For instance TEMP 200 0F is 200 F and TEMP 200 0C is 200 C ALT Altitude whose unit must be consistent with the length unit specified in the FMLUNIT entry of the AEROZ bulk data card Real HOTWALL Character either YES
303. method is computed by matching the wind tunnel measured section loads The AIC weighting matrix generated by the downwash correction method is computed by matching the surface pressures that are either measured by wind tunnel test or compute by CFD The corrected AIC matrix can be used to provide flexible loads due to structural deformation for trim analysis INTRODUCTION 1 13 This page is intentionally left blank 1 14 INTRODUCTION Chapter 2 HOW TO RUN ZONAIR The ZONAIR software system is available for both the workstation UNIX operating system and the personal computer Windows DOS platforms The execution of ZONAIR after proper installation of the code See Installation Notes for instructions is described as follows UNIX In the directory where the input file and the structural Finite Element Method FEM output file the free vibration solutions of the FEM model reside type the following command zonair lt inputfilename gt lt outputfilename gt where lt outputfilename gt is optional An example is shown as follows zonair myjob inp myjob out output files will be placed in the same directory where the job was submitted after the program terminates See Section 2 6 The ZONAIR Script File for a detailed description of this process that takes place during code execution Windows DOS 1 MS DOS command prompt window under Start Programs MS DOS Prompt 2 Inthe directory where the inpu
304. mmand foraeroelastic analysis Aerodynamic Model Input GENAIC Module SPLINE Module Aerodynamic Influence Coefficient Generation AIC Matrices Aerodynamic amp FEM ModelInterconnection foraeroelastic analysis i ll General Engineering Modules 2 Discipline Engineering Modules Performs Trim Analysis Performs Aeroheating Analysis Computes C and Force Moment Coefficients 2 PLTTRIM PLTMODE Graphical Post Processing Output Figure 4 1 ZONAIR Engineering Module Diagram 4 4 BULK DATA DESCRIPTION 4 2 1 AERODYNAMIC MODEL INPUT The bulk data cards used to define the aerodynamic model are listed in the following table Name Description Remarks ACOORD Aerodynamic local coordinate system definition Optional AEROZ Basic aerodynamic reference parameters Required AESLINK Linking a set of AESURFZ bulk data card Optional AESURFZ Aerodynamic control surface definition Optional AUTOBAR Generates a set of CBAR Optional AUTOROD Generates a set of CROD Optional AUTOTIP Tip modeling of a thick wing component Optional AUTOVOR Automatically generates a VORNET macroelement Optional BODY7 22 body macroelement of body like Oplional CAERO7 Aerodynamic thin wing component geometry input Optional CAEROCP Apply a factor to the pressure coefficients on the CAERO7 Optional macroelement
305. mmetric modes IASET is a character string that is the name of the matrix imported either by the DMI bulk data card or ASSIGN MATRIX Executive Control Command modal data contained in the matrix is associated with the anti symmetric modes The number of rows of the matrix must be the same as the number of anti symmetric modes Same as ISSET but for the anti symmetric modal data LABEL GRIDDISP or FORCE The component number of the displacement at the structural finite element grid point whose identification number is specified by ISSET Integer either 1 2 3 4 5 or 6 REMARK Character String up to 16 with no embedded blanks to give description of the trim function Character See Remark 5 Remarks 1 IDFNC is referred to by the TRIMOBJ and TRIMCON bulk data cards to define the objective function and constraint functions for over determined trim systems IDFNC can also be referred to by the TRIM bulk data card through the SET1 or SETADD bulk data card to print out the values of the trim functions 2 TYPE FEM the component loads include the aerodynamic and inertial loads this case the matrix SMGH must be imported by the ASSIGN MATRIX Executive Control Command with MNAME for symmetric trim system trim degrees of freedom involving only NX NY and or QDOT For anti symmetric trim system trim degrees of freedom involving only NY PDOT and or RDOT the matr
306. n Defines the name of a data file in which the data for plotting the aerodynamic results are stored Format and Example 1 2 3 4 5 6 7 8 9 10 PLTCP IDPLT IDAERO TYPE FORM FILENM AEROGM ES Field Contents IDPLT Identification number Integer gt 0 See Remark 1 IDAERO Identification number of an AEROGEN bulk data card Integer gt 0 See Remark 2 TYPE Character string either YES or NO For TYPE YES the control surface deflection angles are included in the plot file Character FORM FORM TECPLOT for generating the TECPLOT file FORM PATRAN for generating the PATRAN neutral results file FORM IDEAS for generating the DEAS universal file FORM FEMAP for generating a FEMAPTM neutral file FORM ANSYS for generating an ANSYS supported neutral file FORM NASTRAN for generating a NASTRAN bulk data deck with PLOAD4 cards to define the pressure loads FORM ESA for generating a PEGASUS readable file Character Default TECPLOT See Remark 3 FILENM The name of a data file in which the data for plotting the aerodynamic pressures is stored This file name is always in the upper case In case the input file name is given in the lower case the program converts it to the upper case If the first character starts with a dollar sign the rest of the characters must be integers This integer is the identification number of an EXTFILE bulk data card where
307. n are FMLUNIT sec where FMLUNIT is the length unit defined by the AEROZ bulk data card for NX NY and NZ and rad sec for PDOT QDOT and RDOT NX NY and NZ are specified in terms of gravity g where PDOT QDOT and RDOT in terms of rad FMLUNIT Translational accelerations along the x y and z axis respectively of the aerodynamic model Character or Real See Remark 5 Three options are available TRNACC G Characters NONE trim degree of freedom associated with the translational acceleration is eliminated from the trim system Characters FREE The translational acceleration is a FREE trim degree of freedom The value of the translational acceleration is unknown and to be solved by the trim system Real Value The translational acceleration is fixed and given by the real value Angular acceleration about the x y and z axis respectively of the aerodynamic model Character or Real See Remark 5 Similar to NX NY and NZ characters NONE FREE or real values can be specified Identification number of a SET1 bulk data card that specifies a set of identification numbers of TRIMFNC or TRIMADD bulk data card All values of the trim functions defined by the TRIMFNC or TRIMADD bulk data card are computed and printed out Integer 0 Identification number of a TRIMVAR bulk data card to define a trim variable Integer gt 0 See Remark 6 Value of the trim variable IDVARi
308. n the structural finite element model MODAL the trim function is evaluated based on the user supplied modal data LABEL Character string that must match one of the following characters For TYPE AERO Characters Description CDL Induced drag coefficient Please see the definition of Cy in the TRIMVAR bulk data card CY Side force coefficient Please see the definition of C in the TRIMVAR bulk data card CL Lift coefficient Please see the definition of C in the TRIMVAR bulk data card CR Roll moment coefficient Please see the definition of C in the TRIMVAR bulk data card CM Pitch moment coefficient Please see the definition of C in the TRIMVAR bulk data card CN Yaw moment coefficient Please see the definition of C in the TRIMVAR bulk data card CP Center of aerodynamic pressure cp xREFC CL BULK DATA DESCRIPTION 4 185 Characters Description NX NY NZ The acceleration of the trim degrees of freedom is defined as a trim function PDOT QDOT or RDOT TRIMVAR The value of a trim variable is defined as the trim function The identification number of the trim variable is specified in the ISSET entry of the TRIMFNC bulk data card LOADMOD The component loads due to the aerodynamic loads at a set of aerodynamic boxes that are specified in SETK entry of the LOADMOD bulk data card is defined as the trim function
309. name on which the aerodynamic panel data is to be exported Character See Remark 3 HEAT Character string up to 8 characters to specify a base file name to store the aeroheating data of panels Character Default THERMAL IDAERO Identification number of an AEROGEN bulk data card whose corresponding aerodynamic force and moment coefficients will be stored on the file AEROFILE Integer gt 0 Remarks 1 The aerodynamic database generated by the GENBASE bulk data card can be used to perform a trajectory analysis of the vehicle 2 Antypical aerodynamic database is shown as follows Card 1 X34 Aerothermodynamic database from M 1 5 to 8 8 Card 2 GEOFIL DAT Card 3 REFC REFB REFS REFX REFY REFZ NO AESURFZ LENGTH UNIT MASS UNIT Card4 3 5304E 02 1 0000E 00 1 0000 00 0 0000 00 0 0000E 00 0 0000 00 0 IN SLIN Card 5 MACH H ALPHA BETA PRATE QRATE RRATE cD cy cL CR CM CN FILE 6 1 5000E 00 0 0000 00 3 0000E 00 0 0000 00 0 0000E 00 0 0000 00 0 0000E 00 4 7686E 03 1 2617 01 1 1027 04 4 6634 01 1 9792E 04 3 3097E 01 0001 5 1500E 00 0 0000 00 3 0000E 00 0 0000 00 0 0000E 00 0 0000E 00 0 0000 00 3 8865E 03 6 9125 01 1 1325 04 7 4989 02 1 9346 04 4 1903E 03 0002 8 8000E 00 0 0000 00 3 0000 00 0 0000 00 0 0000E 00 0 0000E 00 0 0000 00 3 8374E 03 2 8343E 02 1 1386 04 1 9853E 02 1 9353E 04 1 7430E 03 0003 1 5000 00 1 5780E 06 3 0000 00 0 0000 00 0 0
310. nder Output Vectors Deformation select either TOTAL T1 T2 or T3 to be displayed TOTAL is the complete flutter mode shape The modal natural frequency is displayed in the Output Set panel and will also show on the lower left hand side of the screen during animation Click on OK for both windows FEMAP by default animates or deforms the model based on a percentage of the model length To view the actual displacement based on the ZONAIR output set by the MAXDISP entry of the PLTMODE bulk data card open the View Options window select the PostProcessing category select Deformed Style the Options menu and uncheck the of Model Actual checkbox The number of frames and display times of the animation sequence can be set by the View Options PostProcessing Animation Frames and Delay input options NASTRAN Compatible Output The NASTRAN compatible output is saved in standard NASTRAN bulk data format sample is shown in the following figure and is described below BEGIN BULK DEFORMED AERO MODEL OF THE 2TH MODE REPRESENTED BY GRID amp CQUAD4 FROM FILE sample fre GRID 1 1 00 020 000 000 000 00 GRID 2 8 00 011 202 01 1 20 01 Aerodynamic GRID 3 8 00 010 000 00 1 70 01 Grid Points GRID 4 1 00 020 000 000 000 00 GRID 5 1 00 020 000 000 000 00 CQUAD4 1 201 1 2 3 4 CQUAD4 2 201 5 6 7 8 Quadrilateral CQUAD4 3 201 9 10 11 12 Elements CQUAD4 4 201 13 14 15 16 CQUAD4 5 201 17 18 19 20 ENDDATA
311. ne Rigid Body Attachment Zero Displacement Condition SETK i SETI SET2 PANLSTI PANLST2 PANLST3 PLTMODE gt Plot Interpolated Mode List of Structural Grid Points List of Aerodynamic Boxes on Aerodynamic Model Figure 4 3 Bulk Data Interrelationship for Spline 4 2 3 AERODYNAMIC ANALYSIS FOR COMPUTING THE PRESSURE AND FORCE MOMENT COEFFICIENTS The bulk data cards for the aerodynamic analysis are listed as follows Name Description Remarks Defines the flight conditions Required Save or retrieve the aerodynamic influence coefficient matrix for AJISAV stability derivatives Optional CPFACT Specifies a weighting factor to modify the pressure coefficients Optional Maps the wind tunnel measured pressures onto ZONAIR aerodynamic CESPER panels by spline to replace ZONAIR computed pressures Optional FLEXLD Computes the aerodynamic pressure coefficients forces and moments Optional of a flexible aircraft FLOWPT Aerodynamic solutions at flow field points Optional GENBASE Generates an aerodynamic database Optional Imports the structured Computational Fluid Dynamics CFD solution INFCED and replaces that ZONAIR solution by the CFD solution ponat Imports the unstructured Computational Fluid Dynamics CFD INECEDE solution and replaces that ZONAIR solution by the CFD solution Imports the users supplied pressure coefficients via
312. nels of the aerodynamic model The sequence of the J set is the first group of panels starts from all CTRIA3 and CQUAD4 panels that refer to the MATBODY bulk data card with the lowest identification number Within this group of panels CTRIA3 panels are first assigned to the J set then followed by the CQUAD4 panels last group of panels in the J set are those refer to the MATBODY bulk data card with the highest identification number If a thin wing is modeled by the CAERO7 bulk data card the last set of the J set is the panels on the upper side of the CAERO7 macroelement followed by the panels on the lower side of the CAERO7 macroelement see the pressure coefficient output in the standard output file If DMI is an integer this integer is the identification number of a TRIMINP bulk data card that defines the user supplied dC d trim variable Note 1 If DMI option is activated the program computed aerodynamic stability derivatives of the rigid aircraft DCD DCY DCL DCR DCM and DCN are also automatically recomputed by integrating the user supplied dC d trim variable 2 If DMI entry is blank the program computed dC d trim variable is used for the program assigned trim variables and control surface type of trim variables For the user defined trim variables dC d trim variable is assumed to be zero 4 200 BULK DATA DESCRIPTION TRIMVAR For the program assigned trim variable and the control surface type of t
313. ng trailing edge of the 70 degree delta wing is shown below Wake line shed from the wing tip This line should be connected to the vortex roll up sheet inthe wake region This wake sheet is connected to the vortex roll up sheet in the wake region along the wake line shed from the wing tip These program generated CBAR elements are shown in the following figure The program consequently sweeps these CBAR elements into infinity and forms a set of infinite wake sheets Infinite Wake Sheet BULK DATA DESCRIPTION 4 207 VORNET 5 9 ZONAIR always processes the WAKENET bulk data cards prior to the VORNET bulk data cards Therefore if the WAKENET bulk data card is used to generate the wake sheet behind the wing trailing edge a set of internally generated reference grid points due to the WAKENET bulk data card are available can be referred to by the VORNET bulk data cards For the ith vortex roll up line in the wake region GRIDU and GRIDL be the identification numbers of those reference grid points internally generated by the WAKENET bulk data card FOR DIVIDE SET1 these reference grid points must be specified by the user the GRID bulk data cards with entry PS gt 0 and listed in the SET1 bulk data card For DIVIDE COS or EVEN the locations of these NFED internally generated reference grid points are defined by the entries IDSET REFSTRT ROLLUP REFGRID Note that for DIVIDE
314. ng an ABAQUS supported file FORM NASTRAN for generating a NASTRAN bulk data deck Character string to define an output file name where the deformed aerodynamic model and the pressure coefficients including structural flexibility effects are stored If the first character of FILENM starts with a dollar sign rest of the character must be integers This integer is the identification number of an EXTFILE bulk data card where the filename is specified This feature allows for filenames up to 72 characters to be input Character or blank Character string to define an output file name where the flexiblized aerodynamic pressure coefficients on the panel model are stored in the OUTPUTA format If the first character of FILENM starts with a dollar sign rest of the character must be integers This integer is the identification number of an EXTFILE bulk data card where the filename is specified This feature allows for filenames up to 72 characters to be input Character or blank See Remark 4 1 The FLEXLD bulk data card is referred to by a FLEXLD Case Control Command To include the structural flexibility effects it is required to specify the Executive Control Commands ASSIGN FEM and SOLUTION 1 in the Executive Control Section BULK DATA DESCRIPTION 4 85 FLEXLD 2 The aerodynamic pressure coefficients computed by the AEROGEN bulk data card is used as the aerodynamic loads on the rigid aircraft
315. nsteady pressure results For more details please see Section 7 2 PATRAN Compatible Output BULK DATA DESCRIPTION 4 113 INPDMI INPDMI Replaces ZONAIR Solution Description by External Input Imports the users supplied pressure coefficients via a direct matrix input to replace the pressure coefficient computed by ZONAIR Format and Example I 2 3 4 5 6 7 8 9 10 INPDMI IDAERO NAME INPDMI 100 CP DAT Field Contents IDAERO If IDAERO is a positive integer it refers to the identification number of an AEROGEN bulk data card The pressure coefficients at the flight condition defined by the AEROGEN bulk data card with IDZIDAERO computed by the program are replaced by the CFD solution Integer If IDAERO is a negative integer it is referred to by a TRIMINP bulk data card Integer See Remark 1 NAME Character string that matches a matrix name specified by a DMI bulk data card or an ASSIGN MATRIX Executive Control Command This matrix contains only one column The row contains the pressure coefficient of each panel to be imported Character See Remark 2 Remarks 1 The INPDMI bulk data card is used to import the user supplied pressure coefficients on each aerodynamic panel to replace those computed by ZONAIR 2 The row must contain J set number of pressure coefficients where J set is the total number of aerodynamic panels The sequence of the J set is
316. nted constraints at their rotational degrees of freedom Warning The beam spline method can accurately transfer the displacement from the structural grid to the aerodynamic grid But when transferring the aerodynamic forces back the structured grid it does not ensure the conservation of forces Thus if the user wishes to obtain the loads at the structural grid using the PLTTRIM or PLTTIME bulk data cards SPLINE2 is not recommended The user can add additional grid points in the structural model and connect those grid points to the beam structure by rigid elements then uses SPLINE1 SPLINES bulk data card for spline 2 Ifthe macroelement specified in PANLSTi bulk data card is a CAERO7 the spline axis is the y axis of the coordinate system CORD2R with identification number CID In this case the y axis represents a line along which the original structural grid points are located Note that the structure grid point locations are those in the structural finite element model before the ACSID and the FLIP entries of the AEROZ bulk data card are applied If the macroelement is a BODY7 CID is not used and the spline axis is the x axis of the ACOORD bulk data card associated with the BODY7 macroelement 3 Specifying CURV 0 0 gives the agreement with the SPLINE2 of MSC Nastran because that of MSC Nastran does not include the curvature effect of the torsion stiffness of the beam 4 166 DATA DESCRIPTION SPLINE3 SPLINES3 3D Spline
317. number SUBTITLE subtitle LABEL label AERO number BEGIN BULK Bulk Data Section ACSID XZSYM FLIP FMMUNIT FMLUNIT REFC REFB REFS 5 AEROZ 0 YES NO SLIN IN 100 0 200 10500 AERO REFX REFY REFZ AERO 33 333 0 0 ENDDATA Figure 2 2 ZONAIR Input Data Structure Format Executive Control Section The Executive Control Section must be the first section of any ZONAIR input deck The ASSIGN and CEND are required delimiters The keyword ASSIGN triggers the input file processing performed by the software This section contains information such as the filename of the structural finite element method FEM output to be read in type of analysis to be performed i e symmetric anti symmetric boundary condition etc and How TORUNZONAIR 2 3 print options Finally diagnostic routines useful in programming in the ZONAIR environment are specified in this section See Chapter 3 for details of the Executive Control Section Case Control Section The Case Control Section which must be the second section of any ZONAIR input deck is used to define the disciplines to be performed Each case is defined by a subcase that lists flutter disciplines to be performed for that particular subcase title for the entire input deck and subtitles labels for each subcase are defined in this section The BEGIN BULK statement designates the end of the Case Control Section See Chapter 3 for details of the Executi
318. o the three surface grids is discretize by 3 x 4 reference grids Three surface grids Reference grids These 3 4 reference grids and 3 surface grids are connected by 2 4 CSHEAR panels sheet of doublet singularity is placed on each CSHEAR panel to model the vorticity shed from the three surface grids BULK DATA DESCRIPTION 4 73 CSHEAR The PSHEAR bulk data card must exist to impose the constant potential condition on the CSHEAR panels For those CSHEAR panels immediately behind the surface grids two of G1 G2 G3 and G4 must be the surface grids and the other two are the reference grids The rest of the CSHEAR panels are connected by the reference grids Note that for triangular CSHEAR panel G3 G4 must be specified The indices of the four side edges are shown in the following figure where the first side edge is connected by and Gy the second by and the third by G3 and Gy and the fourth G4and Normal vector side edge 4 side edge 3 Side edge 1 Side edge 2 The CROD entry or the CBAR entry for the CBAR element be integer of any combination by 1 2 3 or 4 For instance CROD 134 implies that three CROD elements are placed along the first third and fourth side edges 4 74 BULK DATA DESCRIPTION CTRIA3 CTRIAS3 Triangular Aerodynamic Panel Description Defines a triangular aerodynamic surface panel by three surface grid points
319. od FEM model and the ZONAIR aerodynamic model It consists of four spline methods that jointly assemble a spline matrix These four spline methods include a Thin Plate Spline b Infinite Plate Spline c Beam Spline and d Rigid Body Attachment methods The spline matrix provides the x y and z displacements and slopes in three dimensions at all aerodynamic grids FEM Model Aerodynamic Model Rigid Body Pitch Mode First Wing Bending Mode se First Body Bending Mode NACA 151 07 Wing Body Configuration with Three Structural Modes 1 8 STATIC AEROELASTIC TRIM MODULE The Static Aeroelastic Trim Module provides trim solutions and flexible loads Static Stress Aeroelastic Distribution Deformation INTRODUCTION 1 11 Main Features 1 9 It employs the modal approach for solving the trim system of the flexible aircraft The modal approach formulates a reduced order trim system that can be solved with much less computer time than the so called direct method It is capable of dealing with the determined trim system as well as the over determined trim system more unknowns than the trim equations The solutions of the over determined trim system are obtained by using an optimization technique which minimizes a user defined objective function while satisfying a set of constraint functions For a symmetric configuration symmetric about the x z plane it requi
320. ol Commands Command Description Remark ASSIGN FEM Structural modal data importer Optional ASSIGN 42 5 MATRIX Direct matrix input by INPUTTA format Optional CEND End of Executive Control Section Required DIAG Diagnostic output options Optional Convert the entire computation of the program from DOUBLE single precision to double precision on 32 bit Optional computers Maximum memory in terms of megabytes that is MEMORY allocable by ZONAIR from the heap space Optional SOLUTION Alter the solution sequence Optional Comment statement Optional Executive Control Commands can be written either in lower case or upper case Each command must start from the first column and it must lie within 80 columns For example ASSIGN FEM demol f06 FORM UAI PRINT 2 80 columns T M M As an added option and only one continuation line can be used when entering the ASSIGN FEM and ASSIGN MATRIX Executive Control Commands The continuation line is active if the first line ends in a comma as shown in the following example ASSIGN FEM demol f06 FORM MSC ROUNDARY S IMG t PRINT 1 SUPORT 123 continuation line active if ending in CEND must be the last command in the Executive Control Section Other commands be located arbitrarily in the Executive Control Section 3 2 EXECUTIVE CONTROL
321. ollows 5 102 2 2MGH 1P 5E16 9 d 3 99 855846336E 03 0 000000000 00 0 000000000 00 0 000000000E 00 0 000000000E 00 000000000 00 1 162878605 02 0 000000000 00 2 181833573 03 0 000000000E 00 000000000 00 0 000000000 00 5 625212629 02 0 000000000E 00 0 000000000E 00 000000000 00 0 000000000 00 0 000000000 00 4 825029982 02 0 000000000E 00 000000000 00 0 000000000 00 0 000000000 00 0 000000000 00 6 989890183 03 000000000 00 0 000000000 00 0 000000000 00 0 000000000E 00 0 000000000E 00 215569848E 02 0 000000000 00 0 000000000 00 0 000000000E 00 0 000000000E 00 000000000 00 1 509172999 01 0 000000000 00 0 000000000 00 0 000000000E 00 000000000 00 0 000000000 00 1 093032792 01 0 000000000E 00 0 000000000E 00 000000000 00 0 000000000 00 0 000000000 00 3 930833207 02 0 000000000E 00 000000000 00 0 000000000 00 0 000000000 00 0 000000000E 00 1 210470133E 01 000000000 00 0 000000000 00 0 000000000 00 0 000000000E 00 0 000000000E 00 884292515E 01 0 000000000 00 0 000000000 00 0 000000000E 00 0 000000000E 00 000000000 00 1 173323700 01 0 000000000 00 0 000000000 00 0 000000000E 00 000000000 00 0 000000000 00 2 918305947 02 0 000000000E 00 0 000000000E 00 000000000 00 0 000000000 00 0 000000000 00 7 453748578 02 0 000000000E 00 000000000 00 0 000000000 00 0 000000000 00 0 000000000 00 9 896419781 02 000000000 00 0 000000000
322. om the aerodynamic model Format and Example Field Contents SETID Set identification number Integer gt 0 See Remark 1 INDGRD Identification number of a grid point that is defined as an independent grid point Integer gt 0 See Remark 2 DEPGRD Identification number of a grid point that is defined as a dependent grid point Integer gt 0 Remarks 1 is not referred to by other bulk data cards The existence of the RBAR bulk data card triggers the program to combine two BEM grid points into one point 2 The dependent grid point is removed from the aerodynamic model Its identification number is replaced by that of the independent grid point Note that the PS entries of the dependent grid and the independent grid must be the same 1 a reference grid point cannot be replaced by a surface grid point or vice versa BULK DATA DESCRIPTION 4 155 RBE2 RBE2 Description Wake Condition Behind the Thick Wing and Body Junction Imposes the potential jump condition at grid points that are attached to the wake sheet generated by the thick wing component Format and Example GRIDL CBAR IDTE GRID Remarks Contents Identification number Integer gt 0 See Remark 1 Absolute value of GRIDU is the identification number of a surface grid point GRID bulk data card with entry PS 0 or blank that is at the upper trailing e
323. on due to smart structural actuation for trim analysis Format and Example 1 2 3 4 5 6 7 8 9 10 PZTMODE PZT1 INPUT4 51 Field Contents LABEL Unique alphanumeric string of up to eight characters used to identify the smart structural modes Character See Remark 2 TYPE Type of boundary condition Character See Remark 2 SYM symmetric ANTI anti symmetric ASYM asymmetric MNAME Matrix name that is imported by the ASSIGN MATRIX Executive Control Command or DMI bulk data cards Character See Remark 3 ACTID Not used Remarks 1 PZTMODE is equivalent to AESURFZ bulk data card except that AESURFZ provides the aerodynamic control forces due to control surface deflection whereas PZTMODE gives the aerodynamic control forces due to the structural deformation This structural deformation can be induced by a smart structural type of actuator 2 Among all PZTMODE AESURFZ AESLINK JETFRC and GRIDFRC bulk data cards no duplicated LABEL is allowed 3 matrix imported by the ASSIGN MATRIX Executive Control Command must have one column and g set number 6 number of structural grid points of rows The elements of the matrix are the structural deformation in six degrees of freedom at all structural finite element grids 4 154 DATA DESCRIPTION RBAR RBAR Combines Two Grid Points into One Point Description Combines two grid points into one point by removing one grid point fr
324. on of structural grid points as part of the plot file Active only for aeroelastic analysis Character See Remark 2 Active only if FEMGRID YES The identification numbers of all structural grid points are increased by OFFSET Integer 0 or Blank See Remark 3 FORM TECPLOT for generating a TECPLOT file FORM PATRAN for generating a PATRAN neutral file FORM IDEAS for generating an I DEAS universal file FORM FEMAP for generating a FEMAP neutral file FORM ANSYS for generating an ANSYS supported neutral file FORM NASTRAN for generating a NASTRAN bulk data deck Character default TECPLOT See Remark 4 The name of the data file in which the data for plotting the aerodynamic model is stored This file name is always in the upper case In case the input file name is given in the lower case the program converts it to the upper case Character Character string either YES or NO For WAKE YES the CSHEAR panels generated by the WAKENET or VORNET bulk data card if any are included in the data file Character Default Y ES BULK DATA DESCRIPTION 4 139 PLTAERO Remarks 1 SETID is not referred to by other bulk data cards existence of PLTAERO in the bulk data input triggers the generation of a data file for the purpose of plotting the aerodynamic model SETID is used for error message output only Users may want to graphically display the aero
325. one half of the aircraft ZONAIR superimposes the symmetric solutions and the anti symmetric solutions to obtain the asymmetric solutions of the complete aircraft 4 12 BULK DATA DESCRIPTION The bulk data cards for static aeroelastic trim discipline are listed in the following table Name Description Remarks Defines the flight condition rigid body mass matrix trim Required IPS Me Case Control Command 18 TRIM degrees of freedom and trim variables to perform static erue selected the Case aeroelastic trim analysis Control Section TRIMADD Defines a trim function as a function of other trim Optional functions Defines a set of constraint functions to be satisfied for Required only for the over TRIMCON 4 solving the over determined trim system determined trim system Defines a trim function whose value is depended on the trim Required only for the over 4 variables and trim degrees of freedom determined trim system TRIMINP Replaces the ZONAIR computed pressure derivatives with Optional respect to the trim variable by user supplied values TRIMLNK Defines a set of coefficient and trim variable identification Optional number pairs for trim variable linking Defines an objective function to be minimized for solving Required only for the over TRIMOBJ 6 the over determined trim system determined trim system TRIMSEN Sensitivity an
326. oordinates If YORIGN defined in the ACOORD bulk data card to which the body refers is zero and the XZSYM entry of the AEROZ bulk data card is YES only half of the body on the positive y side is generated Conversely if YORIGN is not zero and the XZSYM entry of the AEROZ bulk data card is YES the points input must be distributed over the entire circumference of the body For both of these cases the y values listed in the AEFACT bulk data card must start with zero and end with zero See the following figures However if the XZSYM entry of the AEROZ bulk data card is NO then the entire body must be input 1 e all circumferential points defined regardless of the value of YORIGN 4 44 BULK DATA DESCRIPTION BODY7 7 Y NRAD Z NRAD YORIGN 0 YORIGN z 0 NRAD 9 2 Z 2 1 Z 1 Y NRAD Z NRAD 1 Z 1 ITYPEi through IDZi entries must be repeated for each axial station of the body 1 NAXIS times therefore ZRi IDYi and IDZi represent the circumferential points at Xi BULK DATA DESCRIPTION 4 45 CAERO7 CAERO7 Aerodynamic Thin Wing Component Description Defines an aerodynamic wing macroelement of a thin wing component Format and Example WID LABEL ACOORD NSPAN NCHORD LSPAN PAFOIL7 ZTAIC XRL YRL ZRL RCH Contents Identification number Integer gt 0 See Remark 1 An arbitrary charact
327. or low angle of attack aerodynamics At high angle of attack condition where the roll up vortex could take off from the wing tip the structures of the roll up vortex should be modeled by the VORNET macroelement Figure 5 13 depicts a typical roll up vortex modeling by the VORNET macroelement which consists of a set of CSHEAR elements for the modeling of the vorticity sheet and a set of CROD elements for the modeling of the vortex core For the detailed description of the VORNET macroelement please refer to the VORNET bulk data card It should be noted that the shape of the VORNET macroelement can be determined by the wake relaxation technique which is similar to the one for the curved wake surface GUIDELINES FOR AERODYNAMIC MODELING 5 7 line vortex vortex core CROD element GRIDU vorticity feeding point vorticity sheet CSHEAR panel GRIDL Figure 5 13 Roll Up Vortex Modeling by the VORNET Macroelement 5 5 2 FOR THE WAKE MODELING BEHIND THE WING BODY JUNCTION Figure 5 14 a shows a wing body configuration where a gap exists between the inboard of the wake from the wing and the body behind the wing body junction As mentioned earlier this gap violates the closure condition because the inboard of the wing becomes a free edge and is therefore incorrect modeling Wake from aes CBAR CROD b Incorrect Modeling c Correct Modeling using a Incorrect Modeling due to the Gap using CROD Along the RBE2 In
328. oundary conditions are specified the number of structural grid points and their locations must be identical between these two finite element models Remark 2 of ASSIGN FEM ZONAIR reads the file a to obtain the free vibration solutions computed by the structural finite element code b Specifically ZONAIR searches for the following data in the file a e the structural grid point locations of the finite element model identification numbers are used for spline These grid point locations and their e coordinate transformations that relate the local or global coordinates to the basic coordinates These coordinate transformations are used to transform the structural grid point locations from the local coordinates to the basic coordinates as well as the modal data from the global coordinates to the basic coordinates for the definition of local global and basic coordinates please see a NASTRAN User s Manual e the natural frequencies the generalized masses the generalized stiffness and the mode shapes EXECUTIVE CONTROL SECTION 3 5 ASSIGN FEM Remark 3 of ASSIGN FEM For MSC NASTRAN UAI NASTRAN CSA NASTRAN or NE NASTRAN the following two commands must exist in the case control deck of the NASTRAN input as well as output file that generates the NASTRAN solution output file a ECHO SORT DISP ALL Please see a NASTRAN User s Manual for a description of these two
329. p Pinp B 6 7 Entropy 5 inp Defining the non dimensional entropy as 5 7 1 Sinp 7 p One common definition for entropy in the CFD world is given by s cont Where const typically equals Poo p p substituting s into B 7 1 and reducing yields BULK DATA DESCRIPTION 4 111 INPCFD1 since the non dimensional density is defined as Pinp given that a2 and p p TR p can be manipulated to give oss B 7 2 P Eqn B 7 2 can be re written as 7 3 Poo Poo substituting into B 7 3 yields P yM 2 2 Ay Des Us Pinp 1 Sinp substituting A 1 yields 2 YM Sinp P fv y d Pinp 8 Pressure pis Defining the non dimensional pressure as oo Pinp d p substituting that p p T R B 7 multiplying the numerator and denominator by yU2 and rearranging yields P we Pinp 5 puU2 since 2 yRT and Ue we have Mo oo 4 112 BULK DATA DESCRIPTION INPCFDI p 2 2 YM eo PooU so substituting A 1 yields Pinp P jwYM amp B 8 PATRAN requires that the aerodynamic model be stored in a neutral file and that analysis results be stored in a results file Therefore the AERONM entry is used to assign a name for a neutral file that contains the aerodynamic model while the FILENM entry specifies a file that will contain the u
330. per side of the wake whereas the other is attached to the lower side as show in the following figure Five CBAR s attached to the panel edges which are on the upper side of the wake sheet eee M Ls Se Five CBAR s attached to the panel edges yes which are on the lower side of the wake sheet These CBAR s generate additional wake sheets extending to infinity so that the gap between the root of the wake sheet and the body can be filled up by these wake sheets BULK DATA DESCRIPTION 4 157 RBE2 Wake from wing It should be noted that these internally generated CBAR elements be individually removed even if the entry CBAR YES This is done by specifying negative identification numbers of two consecutive grid points including GRIDU and GRIDL For instance if GRIDU lt 0 and GRID lt 0 the internally generated CBAR between these two grids is removed 5 The X location of GRID must be from upstream to downstream from the grid point immediately behind the trailing edge of the thick wing component to the grid point at the end of the body In the figure show above GRID 211 311 412 963 and 319 The negative sign of GRID including GRIDU and GRIDL is to avoid the generation of the CBAR elements even if entry CBAR YES This is activated if two consecutive GRID for example both GRID and GRID or both G
331. que box of a wing component A finite element wing model that does not fully extend to the leading and trailing edges of the wing may result an inaccurate spline result due to extrapolation Another typical case is the beam type element model of a fuselage component Since the nose section of a fuselage is often considered a non structural part and therefore requires no structural modeling the beam model may end up shorter than the actual length of the fuselage Extrapolation is performed for the spline of aerodynamic panels located outside the domain of the structural finite element grid points Both of the plate spline methods IPS and TPS and the beam spline method incorporated within the spline module of ZONAIR provide a purely linear extrapolation only if the aerodynamic panel is located far away from the finite element model Otherwise distortions and oscillations may occur in the extrapolation regions For this reason extrapolation should be avoided To circumvent the extrapolation problem it is recommended that extra grid points located at the leading and trailing edges of the wing or at the nose of the fuselage be added in the structural finite element model These grid points can then be connected by rigid elements to their adjacent grid points Thus the problem associated with extrapolation can be avoided As a final note graphical display of the displacements on the aerodynamic model for spline verification is highly recommended It i
332. quired FORM b FORM indicates the format of the data on the external file Optional default FORMAT b FORMAT for non sparse and ASCII with 5E16 9 format b FORMAT23 for non sparse and ASCII with 3D23 16 format b UNFORMAT for non sparse and binary format b SFORMAT for sparse and ASCII format Note that sparse and binary format is not allowed MNAME indicates that is the name of the matrix up to 8 characters The matrix on the external file a is read in and written on the runtime database as a matrix entity with name 2 c If MNAME is not specified the name of the matrix specified in the header record of the INPUTTA format is used as the name of the matrix Optional PRINT n Print option to the output file where n is an integer 0 no printout of matrix n 0 print out the matrix If no PRINT is specified n 0 is used as a default Optional 3 20 EXECUTIVE CONTROL SECTION ASSIGN MATRIX ASSIGN MATRIX is an optional Executive Control Command for direct matrix input The format of the matrix data stored on the external file is very similar to that of the INPUTT4 or OUTPUT4 module of NASTRAN except for the following differences e Sparse and binary format is not allowed For non sparse and ASCII format the FORTRAN format of the matrix data must 5E16 9 The options of format are presented as follows For Non Sparse and ASCII Form
333. r gt 0 A factor applied to C Real 7 0 0 or Blank Default 1 0 A offset for the centroid of the panel along the x y and z direction respectively Used only in the separation process of panels into upper and lower groups by the RBE2 and SLICE bulk data card or a attached to a body Real Default 0 0 see Remark 3 BULK DATA DESCRIPTION 4 151 PSHELL Remarks 1 PSHELL bulk data card is referred to by the CQUAD4 CTRIA3 bulk data cards 2 the inclination angle of the panel exceeds the Mach cone angle in supersonic hypersonic flow Mach cone angle sin 1 where M free stream Mach number the linear theory fails This kind of panel orientation is classified as superinclined panel Special treatment will be performed by the program to circumvent the superinclined panel problem if incline 0 3 When a RBE2 SLICE bulk data card is used or a CAERO7 macroelement is attached to a body the program needs to separate those involved CQUAD4 CTRIA3 panels into upper surface and lower surface groups This separation process may fail and cause a fatal error printed in the output file as follows THE PROGRAM FAILED TO SEPARATE THOSE PANELS SURROUNDING THIS GRID INTO UPPER amp LOWER GROUPS Shown in the following figure is CAERO7 attached to two CQUAD4 panels because the centroid of both panels points A and B are located the upper side of the CAEROT this separation process with fai
334. r generating a PATRAN neutral file FORM IDEAS for generating an I DEAS universal file FORM FEMAP for generating a FEMAP neutral file FORM ANSYS for generating an ANSYS supported neutral file FORM NASTRAN for generating a NASTRAN bulk data deck PLOAD4 cards to define the aeroheating results FORM ESA for generating a PEGASUS readable file Character Default TECPLOT The name of the data file in which the data for plotting the aeroheating results is stored This file name is always in the upper case In case the input file name is given in the lower case the program converts it to the upper case If the first character starts with a dollar sign the rest of the characters must be integers This integer is the identification number of an EXTFILE bulk data card where the filename is specified This feature allows for filenames up to 72 characters to be input Character See Remark 3 The name of a data file in which the aerodynamic model is stored in a PATRAN neutral file ONLY USED IF FORM PATRAN Character Default AEROGEOM PAT See Remark 4 4 172 DATA DESCRIPTION THERMAL The THERMAL bulk data card is referred to by a THERMAL Case Control Command that invokes the program to compute the aeroheating results These results include temperature heat flux skin friction coefficient pressure and flow transition from laminar flow to turbulent flow distribut
335. r of the TRIM bulk data card Integer 0 This TRIM bulk data card must exist in the Bulk Data Section TRIM and n must be separated by an equal sign For a symmetric trim system trim system involving only the longitudinal degrees of freedom with structural flexibility the free vibration solution of the finite element model with symmetric boundary condition must be imported by the ASSIGN FEM Executive Control Command with BOUNDARY SYM For an anti symmetric trim system trim system involving only the lateral degrees of freedom the free vibration solution of the finite element model with anti symmetric boundary condition must be imported by the ASSIGN FEM Executive Control Command with BOUNDARY For an asymmetric trim system trim system involving both the longitudinal and the lateral degrees of freedom both free vibration solutions must be imported However for an asymmetric configuration entry XZSYM NO in the AEROZ bulk data card only one ASSIGN FEM Executive Control Command with BOUNDARY ASYM is required Computing the distributed inertial loads resulting from the trim system requires a matrix called for symmetric or asymmetric structural boundary condition and a matrix called for anti symmetric structural boundary condition to be inputted by the ASSIGN MATRIX Executive Control Command These matrices are the product of the G set mass matrix an
336. railing edge and tip Figure a into an opened trailing edge and tip model To achieve this the program will automatically generate a set of grid points that are attached to those panels on the lower surface Note that the identification numbers of this set of grid points start with EID The user must ensure that there is no duplicated identification number between this set of grid points and the other grid points A set of CBAR elements will be automatically generated and attached to the upper and lower surface of the opened trailing edge However this generation of CBAR elements along the trailing edge can be deactivated by specified a negative EID set of CROD elements are BULK DATA DESCRIPTION 4 161 SLICE also automatically generated and attached to the upper and lower surface along the opened wing tip Figure b DIRECTI ENDRG STARTG DIRECT2 a Closed wing trailing b Opened wing trailing edge and tip edge and tip 2 be equal to STARTG to deactivate the slicing action along the trailing edge In addition ENDBG can be a negative integer This can deactivate the generation of a grid point at ENDBG 1 the edge at ENDBG is still closed 3 If the grid point ENDBG is located at the trailing edge of the wing body junction RBE2 must be YES or NOCBAR to automatically create the trailing wake along the surface grid points behind the wing body junction For NOCBAR the entry CBAR in th
337. ral file that contains the aerodynamic model while the FILENM entry specifies a file that will contain the displacement or steady pressure results depending on whether TYPE DEFORM or 4 148 DATA DESCRIPTION PSHEAR PSHEAR Properties of the CSHEAR Panel Description Imposes the constant potential condition on the CSHEAR panels and relates the values of the constant potential to that at a surface grid Format and Example 1 2 3 PSHEAR MATWAKE 4 5 6 7 8 9 10 GRIDA SIDEA GRIDB SIDEB ATTACH Field PID MATWAKE GRIDA SIDEA GRIDB SIDEB ATTACH EPS Remarks Contents Unique identification number Integer gt 0 See Remark 1 Identification number of a MATWAKE bulk data card Integer gt 0 Identification number of a surface grid where the potential of the SIDEA edge of the CSHEAR panel is originated Integer gt 0 Index of the four side edges of the CSHEAR panel along which the potential is constant and equal to that at the surface grid GRIDA Integer 1 2 3 or 4 See Remark 2 Same as GRIDA but for the second index of the SIDEB edge Integer gt 0 The second index of the side edge Integer 1 2 3 or 4 The identification number of a CQUADA or CTRIA3 panel where the surface grids GRIDA and GRIDB are located Integer gt 0 or Blank See Remark 3 Small tolerance to detect the skewness of the CSHEAR panel Real gt 0 0 Default 0 001
338. rates a set of CROD elements between two surface grid points Format and Example i 2 3 4 5 6 Zi 8 9 10 AUTOROD EID STARTG ENDG DIRECTG AUTOROD 100 30 5a 0 Field Contents EID Unique identification number Integer gt 0 See Remark 1 STARTG Identification number of a surface grid point that is located at the trailing edge of the wing tip Integer gt 0 ENDG Identification number of a surface grid point that is located at the leading edge of the wing tip DIRECTG Optional Input DIRECTG is the identification number of a surface grid point to define the initial search vector Integer 0 See Remark 2 Remarks 1 The AUTOROD bulk data card automatically generates a set of elements between the grid points STARTG and ENDG CROD elements are automatically generated DIRECTG ENDG STARTG Initial Search Vector 2 The initial search vector is from the grid point STARTG to the grid point ENDG The initial search vector directs the search procedure to find all grid points between STARTG and ENDG 4 34 BULK DATA DESCRIPTION AUTOTIP AUTOTIP Tip Modeling of a Thick Wing Component Description Defines an aerodynamic macroelement for the modeling of the tip of a thick wing component Format and Example 1 2 3 4 6 7 8 9 10 AUTOTIP EID GRIDS PANELS RODS PSHELL T
339. rd is active only if the SOLUTION 1 Executive Control Command is specified Format and Example Field Contents EID Unique element identification number Integer gt 0 See Remark 1 MODEL Not used CP Not used SETK Refers to PANLSTI PANLST2 or PANLST3 bulk data card that lists the aerodynamic panel identification numbers Integer gt 0 Remarks 1 EID is only used for error output SPLINEO is used only for computing the flexible loads 2 A typical case of imposing the zero displacement condition on aerodynamic panels 1s the modeling of the wind tunnel wall on which a zero displacement condition 1s desired Since the panels representing the wind tunnel wall are not attached to the structural model the zero displacement condition can be specified by using the SPLINEO bulk data card 4 164 DATA DESCRIPTION SPLINE1 SPLINE1 Surface Spline Method Description Defines an infinite plate spline method for displacements and loads transferal between CAERO7 macroelement and structural grid points The SPLINE1 bulk data card is active only if the SOLUTION 1 Executive Control Command is specified Format and Example 1 2 3 4 5 6 7 8 9 10 Field Contents EID Unique element identification number Integer gt 0 See Remark 1 MODEL Not used CP Coordinate system defining the spline plane Integer 2 0 or blank See Remark 2 SETK The identification number of a PANLST1
340. rd Set 1 NGRID Free Format NGRID Number of grid points Integer gt 0 Card Set 2 X y Z Free Format 2 Location of the flowfield point Repeat Card Set 2 NGRID times Comment card may be used and must be initiated with a in the first column For FORM TECPLOT the TECPLOT format is used to define the flowfield point mesh Multiple zones are allowed and the mesh can be either POINT or FEPOINT For output the aerodynamic solutions U V W C and Mach numbers are stored at each point BULK DATA DESCRIPTION 4 89 FOILSEC FOILSEC NACA Airfoil Section Description Defines an NACA series type of airfoil section Format and Example 2 3 4 5 6 7 COEFF PROFILE FIRST SECOND THIRI etc Ese Field ID COEFF PROFILE Contents Identification number that is referred to by a PAFOILS bulk data card Integer gt 0 See Remark 1 real coefficient to multiply to the airfoil section Real gt 0 0 See Remark 2 Character string either NACA or USER For TYPE NACA airfoil is an NACA series type of airfoil section For TY PE USER airfoil is a user defined airfoil section Character Default NACA Character string For TYPE NACA PROFILE can be one of followings 4 5 5M 16 63 63 64
341. rd is used to import the CFD solution from a structured CFD code This feature allows ZONAIR to compute more accurate incremental aeroelastic loads due to structural flexibility effects using CFD generated rigid loads Because the CFD mesh may be oriented in an arbitrary fashion with respect to the aerodynamic model it 18 required to transform the CFD mesh so that the CFD surface mesh and the ZONAIR aerodynamic model overlap with each other This can be achieved by introducing a CORD2R bulk data card with identification number TRANSF that defines a coordinate system where the CFD mesh is located In the following figure the X Y Z system is the local coordinates defined by a CORD2R bulk data card whereas 2 15 the aerodynamic coordinates of the ZONAIR aerodynamic model y y CFD Mesh ZONAIR ZONAIR 22227 94 Aerodynamic rcs erodynamic Model NJ Model 7 i Points of CORD2R X X Definition In the example the nose of the fuselage of the CFD surface mesh is located at x z 0 and y 100 with respect to the ZONAIR aerodynamic model whereas that of the ZONAIR aerodynamic model at 2 0 To transform the CFD mesh it is required to specify CORD2R bulk data card such as CORD2R 50 0 0 100 0 0 0 0 0 100 0 1 0 C C 0 0 101 0 1 0 In addition because the above figure shows that the CFD surface mesh is located in the negative axis the entry TRANSF must be
342. rds All CSHEAR panels that refer to the PSHEAR bulk data card and the MATWAKE bulk data card are grouped into one curved wake surface In the following example the CSHEAR panels 101 102 104 and 205 are grouped into one curved wake surface called TEWAKE CSHEAR 101 1 PSHEAR 1 100 CSHEAR 102 1 MATWAKE 100 TEWAKE CSHEAR 104 10 PSHEAR 10 100 CSHEAR 205 10 BULK DATA DESCRIPTION 4 123 OMITCFD OMITCFD Defines the Surface Mesh Description Defines the surface mesh index of a structured CFD mesh to avoid the reading of all CFD grid points into the computer memory Format and Example 1 2 3 4 7 8 5 6 9 cowr soc ren semen zem starr Conr suck sano xm ss deee S 1 1 rum OMITCFD 1 133 TECPLOT SURFACE PLT SOLUTION PLT 3 Po am s s a Field Contents IDOMIT Identification number that is referred to by an INPCFD bulk data card Integer gt 0 See Remark 1 GAMMA Specific heat ratio used in the CFD computation Real gt 1 0 default 1 4 FORM Format of the output file specified in the entry FILENM FORM TECPLOT for generating a TECPLOT file FORM PATRAN for generating a PATRAN neutral file FORM IDEAS for generating a I DEAS universal file FORM FEMAP
343. re 5 6 Requirement of Panel Coherence for Continuous Doublet Distribution This implies that any grid point in the aerodynamic model must be completely surrounded by panels and the entire panel model must be closure i e no hole or slit is allowed For instance the engine inlet face must be closed by panels even if physically it is a hole ZONAIR allows the flow to penetrate into those panels to simulate the effects of the inlet by imposing the in flow condition which is specified in the PSHELL bulk data card However along the trailing edge of a wing and a truncated end body or along the tip of a wing where a free edge exists this closure condition can not be satisfied because the physical surface ends along those free edges To satisfy the closure condition requires adding a wake surface or vortex roll up line along these free edges 5 4 GUIDELINES FOR AERODYNAMIC MODELING 5 3 WAKE MODELING Physically the wake surface is a thin layer of surface containing vorticities due to the rotationality of the flow ZONAIR models this thin vorticity layer by a doublet sheet with an infinitesimal thickness and with a constant doublet strength along the streamwise direction This type of doublet sheet is called the wake surface The wake surface usually starts from the trailing edge of a wing or the rear end of a truncated end of body to simulate the vorticities shaded from those edges There are two types of wake surfaces that can be used
344. red surface panel scheme that is compatible to the finite element methods This enables the direct adoption of off the shelf finite element pre and post processors such as PATRAN I DEAS etc for ZONAIR panel model generation The specific capabilities of ZONAIR include A unified high order subsonic supersonic hypersonic panel methodology as the underlying aerodynamic force generator Unstructured surface panel scheme compatible to the finite element method Direct adoption of off the shelf FEM pre and post processors for rapid panel model generation Vortex roll up scheme for high angle of attack aerodynamics Trim module for flexible loads and aeroheating module for aeroheating analysis Pressure mapping from CFD mesh to ZONAIR panels AIC correction using wind tunnel measured loads for accurate flexible loads generation Aerodynamic and loads database for 6 d o f simulation and critical loads identification ZONAIR consists of many submodules for various disciplines that include 1 AIC matrix generation module 2 3 D spline module 3 trim module 4 aeroheating module 5 vortex roll up module and 6 aerodynamic stability derivative module The interrelationship of ZONAIR with other engineering software systems such as the pre processor structural finite element method FEM Computational Fluid Dynamic CFD method six degree of freedom 6 d o f and critical loads identification is depicted in Figure 1 1 FEM sol
345. rence parameters Format and Example IAEROZ ACSID XZSYM FLIP FMMUNIT FMLUNIT REFC REFB REFS CONT CONT AEROZ AEROZ Field ACSID XZSYM FLIP FMMUNIT FMLUNIT REFC REFB REFS REFX REFY REFZ Contents Identification number of a CORD2R bulk data card defining a coordinate system where x axis is toward the pilot s face from a pilot situated in the finite element model and y axis is on the pilots right hand side Used only if the Executive Control Command SOLUTION 1 is specified Integer gt 0 or Blank See Remark 2 Character string either YES or NO YES the aerodynamic model is symmetric about its 2 plane this implies that only the half model on the right hand side 1s described NO both the right and left hand sides of the aircraft are modeled Character Default YES See Remark 2 Character string either YES or NO YES the structural model is on the left hand side of the pilot but aerodynamic model is on the right hand side Used only if the Executive Control Command SOLUTION 1 is specified Character Default NO See Remark 2 Not used Units of mass used in the structural finite element model This parameter is automatically assigned by the program to be LBF if English units are used or N if metric units are used on the FMLUNIT entry Note that if FMLUNIT is assigned to be NONE the program will automatically set FMMUNI
346. res only the modeling of one half of the configuration even for the asymmetric flight conditions It generates the flight loads on both sides of the configuration in terms of forces and moments at the structural finite element grid points in terms of NASTRAN FORCE and MOMENT bulk data cards for subsequent detailed stress analysis PRESSURE MAPPING FROM CFD MESH TO ZONAIR PANELS Main Features It interpolates the surface pressure coefficient from the CFD surface mesh onto the ZONAIR panels and use this pressure to generate the rigid loads for trim analysis ZONAIR can further transfer this rigid loads from the ZONAIR panel to the structure finite element grid points using the spline module It also interpolates the surface velocities that are used for the streamline calculation for aeroheating analysis Shown below is the comparison of Cp between the CFD results and the interpolated ZONAIR results on X 34 at M 10 a 5 CFL3D Mesh ZONAIR Panel Model CFL3D Cp Mapped Cp on ZONAIR Panels 1 12 INTRODUCTION 1 10 AIC CORRECTION MODULE FOR ACCURATE FLEXIBLE LOADS GENERATION Main Features The AIC correction module computes an AIC weighting matrix to modify the ZONAIR computed AIC matrix for accurate flexible loads generation It adopts the force moment correction method by Giesing et al and the downwash correction method by Pitt and Goodman The AIC weighting matrix generated by the force moment correction
347. rim variables the SYM entry is ignored since the types of the aerodynamic stability derivatives are already defined by the trim variables For the user defined trim variables the SYM entry must be specified d C pep amp _ poy se d trim variable d trim variable per MC pcr d trim variable d trim variable d TEE eh AS DCN d trim variable d trim variable Note For the user defined trim variables DCD DCY DCL DCR DCM and DCN cannot be NONE Thus all aerodynamic stability derivatives of the user defined trim variables must be specified by real values BULK DATA DESCRIPTION 4 201 VISCOUS VISCOUS Viscous Vortex Model Description Defines the viscous parameters for computing the skin frictions and introducing the viscous vortex model of the line vortex CROD elements Format and Example 1 2 3 4 5 6 7 8 9 10 Field Contents SID Unique identification number Integer gt 0 ALT Character string or real number If ALT is a real number ALT is the altitude at which the viscous parameters entries VIS DENS VEL and PRES are automatically computed based on the standard atmospheric table i e VIS DENS VEL and PRES are not required for input Note that the units of ALT is in FMLUNIT where FMLUNIT is the length unit of the aerodynamic model defined in the AEROZ bulk data card If ALT The viscous parameters are defined in t
348. rix SYM Symmetric matrix Note that if FORM SYM only the upper triangular part of the matrix including the diagonal is allowed for input 4 GCOL and CCOL define the column index The column index can be calculated by 6xn CCOL where n is the number of structural grid points whose identification numbers are smaller than GCOL 5 GROW and CROW define the row index of the matrix The row index can be calculated by 6xn CROW where n is the number of structural grid points whose identification numbers are smaller than GROW 6 The column index and row index can uniquely define the location of xj and for complex matrix in the matrix All terms in the matrix that are not specified in the DMIG bulk data card will be zero The mass unit and the length unit involved in the terms must be consistent with the FMMUNIT and FMLUNIT entries defined in the AEROZ bulk data card BULK DATA DESCRIPTION 4 79 DMIL DMIL Matrix Element Value Definition by Large Fields 16 Column Fields Description Defines the values of matrix elements by 16 column fields DMIL is referred to by DMI bulk data cards Format and Example Field Contents NAME Name of the matrix NAME must be the same as the entry NAME of the DMI bulk data card Character J Column number of NAME Integer gt 0 I1 I2 etc Row number of NAME which indicates the beginning of a group of nonzero elements in the column Integer gt 0 A Ix J
349. root chord divisions of the wing component in percentage of the root chord The number of values listed in AEFACT must be NCHORD and must start with 0 0 and end with 100 0 If LRCHD 0 then NCHORD evenly distributed chordwise divisions for the root is used Integer 2 0 For ATTR YES LRCHD is the identification number of a SET1 bulk data card that lists NCHORD identification number of the surface grid points GRID bulk data card with entry PS 0 or Blank Integer gt 0 Note that LRCHD can also be a character string AUTO that triggers the program to automatically search for the surface grid points located along the wing body junction Character AUTO See Remark 4 Identification number of a SET1 bulk data card that lists a set of identification numbers of the surface grid points These grid points are located behind the root of the thin wing component where the wake from the wing root is attached Integer 0 Note that the RWAKE can also be a character string AUTO that triggers the program to automatically search for the surface grid points located behind the root of the thin wing component Character AUTO See Remark 5 X Y and Z location of the tip chord leading edge Real See Remark 6 Length of the tip chord Real Same as ATTR but for the tip of the thin wing component Character Same as LRCHD but for the tip of the thin wing component Integer 2 0 Same as RWAKE but for the tip of t
350. rtex sheet by following the left hand rule about the vortex line Otherwise it follows the right hand rule Integer Z 0 ANGLE An angle in degrees to define the location of the vortex core line where the CROD elements are located This angle is defined by the angle between the vortex core and the x axis Based on numerical experience this angle should be half of the angle of attack specified in the AEROGEN bulk data card Real gt 0 0 CANT A cant angle in degrees between the vector from the surface grid to the vortex core and the z axis Real ROLLUP Character string LINE or CIRCLE to define the shape of the roll up vortex line Character Default CIRCLE NFED Number of vortices feeding points along each vortex roll up line Integer gt 0 See Remark 2 CBAR Character string either YES or NO For CBAR YES a set of CBAR elements are automatically generated and attached to the last vortex roll up line See description of Remark 4 of the VORNET bulk data card Character Default YES 4 38 BULK DATA DESCRIPTION AUTPVOR GRIDi If GRID is an integer GRIDi is a list of the identification numbers of the surface grid points that are in the downstream of the grid point TIPGRID Thus the vortex roll up sheet starts from TIPGRID and progresses along GRIDi Therefore x location of GRIDi must be in the ascending order The program will slice those panels along GRIDi into two sets of panels
351. ry body Integer 1 2 or 3 See Remark 6 Xi x location of the axial station Xi must be in ascending order 1 1 1 gt Real CAMi Body camber at the Xi axial station Real YRi Body cross sectional radius if ITYPEi 1 or the semi axis length of the elliptical body parallel to the y axis if ITYPEi 2 Real Note that YR must be 0 0 ZRi The semi axis length of the elliptical body parallel to the z axis Real Note that ZR must be 0 0 BULK DATA DESCRIPTION 4 41 BODY7 IDYi IDZi Identification number of AEFACT bulk data card that specifies NRAD number of the y coordinate locations of the circumferential points at the Xi axial station Integer gt 0 Note that at X the AEFACT bulk data card must contain only one y coordinate location to represent the body nose Identification number of AEFACT bulk data card that specifies NRAD number of the z coordinate locations of the circumferential points at the Xi axial station Integer gt 0 Note that at X the AEFACT bulk data card must contain only one z coordinate location to represent the body nose See Remark 7 Remarks 1 The BODY7 bulk data card triggers the program to generate a set of CQUAD4 CTRIA3 panels and set of grid points The identification numbers of these panels and grids are numbered sequentially beginning with BID For instance if BID 101 then the identification numbers of the CTRIA3 CQUADA panels and grids are 101 1
352. ry condition respectively at the structural grid points along the center line plane of the fuselage Each boundary condition gives different natural frequencies and mode shapes For symmetric and anti symmetric boundary conditions it is usually required to perform the aeroelastic analysis separately But this is not the case for ZONAIR ZONAIR can compute the Aerodynamic Influence Coefficient AIC matrices for both boundary conditions simultaneously without costing significant additional computer time Therefore it is more efficient when both symmetric and anti symmetric free vibration solutions are included with one ZONAIR analysis Remark 10 of ASSIGN FEM If the SUPORT entry is activated the program will transform the rigid body modes computed by the finite element analysis from the generalized coordinates to the body axis coordinates but leaves the elastic modes unaltered In the body axis coordinates all translational rigid body modes have a value of one in their respective translational degrees of freedom and zero in other degrees of freedom Whereas all rotational rigid 3 18 EXECUTIVE CONTROL SECTION ASSIGN FEM body modes have a unit rotation angle about their respective rotation degrees of freedom whose rotation center is located at REFX REFY and REFZ specified by the AEROZ bulk data card Consequently the generalized mass matrix associated with the rigid body modes are also transformed into the body ax
353. s represented by the symbol F shown in the above equation Integer gt 0 S and E Real coefficients shown in the above equation Real Note E cannot be zero GTORLT Character string either GT or LT Character GT represents that F S must be greater than V LT represents that F S must be less than V VALUE Constraint value represented by the symbol V shown in the above equation Real Remarks 1 IDCONS is referred to by the TRIM bulk data card The TRIMCON bulk data card is active only for the over determined trim system All G serve as a set of constraint functions that must be satisfied simultaneously by the trim variables 2 Since F 5 could be negative the user must select proper values of E to avoid complex number resulting from the constraints functions 4 184 DATA DESCRIPTION TRIMFNC TRIMFNC Trim Function Description Defines a trim function whose value is dependent on the trim variables and trim degrees of freedom Format and Example 1 2 3 4 5 6 7 8 9 10 TRIMFNC IDFNC TYPE LABEL ISSET IASET REMARK TRIMFNC MODAL MATRIXR MATRIXL STRESS AT CBAR Field Contents IDFNC Unique identification number Integer gt 0 See Remark 1 TYPE Character string One of AERO FEM or MODAL Character TYPE AERO the trim function is evaluated based on the aerodynamic model TYPE FEM the trim function is evaluated based o
354. s CBAR 5 flat wake surface by specifying two CQUAD4 Quadrilateral aerodynamic surface panel Optional CROD Line Vortex element Optional CSHEAR Wake panel on the curved wake surface Optional CTRIA3 Triangular aerodynamic surface panel Optional EXTFILE Defines a character string as the name of an external file Optional FOILSEC Defines an NACA series type of airfoil section Optional GRID Location of a surface or a reference grid point AS a JETFRC Control force due to jet Optional JOINTHK Join Two THKWING s Optional BULK DATA DESCRIPTION 4 5 Name Description Remarks Aerodynamic component grouping set of edu dut UBODE CQUAD4 CTRIA3 panels COUP TIAS bulk data card exists MATWAKE Label of a curved wake surface CSHEAR bulk data card exists Defines airfoil cross sections at the root and tip of a PAFOIL7 CAERO7 Optional PAFOILS Alternative form of the PAFOIL7 bulk data card Optional Required if CSHEAR PSHEAR Properties of the CSHEAR panels cati exists Required if PSHELL Properties of the CQUAD4 CTRIA3 panels CQUADA CTRIA3 exists PZTMODE Control forces due to smart structural actuation Optional RBAR Combines two grid points into one point Optional RBE2 Wake condition behind the thick wing and body junction Optional RELAXW Wake relaxation Optional SLICE Slice a closed wing trailing edge Optional THKWING Aerodynamic thick
355. s ZONAIR supports both the older and newer versions of I DEAS output formats The following table lists allowable data sets for modal data input to ZONAIR Data Set No Description 781 and or 2411 Nodes i e GRID points Eigenvector information including frequency and modal mass i e structure mode shapes 55 and or 2414 18 and or 2420 Coordinate systems Data sets other than those in the table above may appear in the universal file and are ignored ZONAIR output plot files in universal file format are also supported which can be directly viewed by I DEAS Please see the PLTxxxx bulk data cards in Chapter 4 for descriptions 3 12 EXECUTIVE CONTROL SECTION ASSIGN FEM A sample output file of the universal file format is shown below zu 2420 8 Demo 1 0 8 CS1 1 0000000000000000D 000 0 0000000000000000D 000 0 0000000000000000D 000 0 0000000000000000D 000 1 0000000000000000D 000 0 0000000000000000D 000 0 0000000000000000D 000 0 0000000000000000D 000 1 0000000000000000D 000 0 0000000000000000D 000 0 0000000000000000D 000 0 0000000000000000D 000 111 0 8 CS111 9 9999999999999989D 001 0 0000000000000000D 000 0 0000000000000000D 000 0 0000000000000000D 000 0 0000000000000000D 000 1 0000000000000000D 000 0 0000000000000000D 000 1 0000000000000000D 000 0 0000000000000000D 000 0 0000000000000000D 000 0 0000000000000000D 000 0 0000000000000000D 000 1 1 2411 10101 1 T 1 3 0000000000000000D
356. s incorporated in ZONAIR The CAERO7 bulk data card distributes a sheet of source singularity and vortex singularity on the mean plane of the thin wing where the source singularity simulates the thickness effects and the vortex singularity simulates the angle of attack and camber effects Figure 5 15 It should be noted that this mean plane is a flat surface that has no camber even for a cambered wing The camber effects are introduced in the boundary condition in the small disturbance sense Source singularity Vortex singularity Figure 5 15 Source and Doublet Sheets on the Mean Plane of the Thin Wing Modeling The CAERO bulk data card divides the mean plan of the thin wing into several strips by the user specified spanwise divisions Each spanwise division must be parallel to the x axis of the aerodynamic coordinate system Each strip is then divided into several boxes called wing boxes by chordwise divisions specified at the root and the tip chords Each CAERO7 bulk data card represents a wing macroelement comprising n 1 X m 1 wing boxes where n the number of spanwise divisions and m the number of chordwise divisions Figure 5 16 presents a typical thin wing configuration modeled by the CAERO7 macroelement The solid circles on each wing box represent the control points at which boundary conditions are imposed The control points which lie along the mid span of each wing box is located at 8596 of the wing box chord for subsonic M
357. s and the aerodynamic analysis are subject to different engineering considerations the grid point locations of these two models may be considerably different This gives rise to the problem of transferring the displacements and forces between these two grid systems Four spline methods are incorporated in the spline module of ZONAIR which generate spline matrices to perform the displacement and force transferal between the structural finite element model and the ZONAIR aerodynamic model These four spline methods are gt Infinite Plate Spline IPS Method by the SPLINEI bulk data card gt Beam Spline Method by the SPLINE2 bulk data card gt Thin Plate Spline TPS Method by the SPLINE3 bulk data card gt Rigid Body Attachment by the ATTACH bulk data card The generation of the spline matrix is performed on a component by component basis The selection of the spline method for a given component depends on the type of component in the ZONAIR model i e wing like or body like component and the type of elements i e beam or plate element used in the finite element model For instance if a body like component is modeled in the ZONAIR model and if beam type elements are used for the finite element model then the beam spline method should be employed If wing like components are modeled in the ZONAIR model and plate type elements are used for the finite element model then the IPS method should be used The TPS method is a 3 D spline method that c
358. s for this reason that ZONAIR provides an option to generate output files containing the aerodynamic panel and corresponding displacement data using the PLTMODE bulk data card Visual inspection of the displacements for both the aerodynamic and the finite element models would minimize errors caused by incorrect implementation of the spline MODELING GUIDELINES OF SPLINE FOR FLEXIBLE LOADS 6 5 This page is intentionally left blank 6 6 MODELING GUIDELINES OF SPLINE FOR FLEXIBLE LOADS This section describes the ZONAIR output files generated for plotting purposes Chapter 7 PLOT FILES Output plot files are generated by the existence of any of the following bulk data cards within the bulk data input section PLTAERO PLTCP PLTMODE and PLTTRIM Table 2 1 presents the output plot file capability of the ZONAIR software system Category Associated Bulk Data Card Description Software Compatibility Aerodynamic Model PLTAERO Generates ASCII text file for plotting the aerodynamic model PATRAN TECPLOT I DEAS FEMAP ANSYS NASTRAN Pressures PLTCP Generates ASCII text file for plotting the pressure coefficients PATRAN TECPLOT I DEAS FEMAP ANSYS NASTRAN PEGASUS Interpolated Structural Modes PLTMODE Generates ASCII text file for plotting the interpolated structural mode on the aerodynamic model PATRAN TECPLOT I DE
359. scheme where the advantages of adopting the unstructured grids is shown unstructured grids is that it allows arbitrary grid point selection for a given configuration demonstrate this feature a sphere is modeled by using regularly spaced shaped panels called Regular Panels and randomly spaced shaped panels called Random Panels whose pressure distribution results are shown in Clearly this arbitrary grid point selection capability of the unstructured grids can greatly reduce the user burden in the grid generation process The similarity between the ZONAIR and MSC NASTRAN input format enables the direct adoption of the pre and post processors of MSC NASTRAN for ZONAIR model generation and result display There are many off the shelf NASTRAN pre and post processors such as PATRAN AEROLAB I DEAS FEMAP etc that are all capable of importing IGES files from the CAD systems Therefore one can generate a ZONAIR aerodynamic model that is based on the surfaces defined by the CAD system rendering a tremendous saving of model generation Figures 1 8 a and 1 8 b respectively effort DIRECT ADOPTION OF OFF THE SHELF FEM PRE PROCESSOR FOR Another advantage in using 1 4 INTRODUCTION In order to ZONAIR Unstructured Grids 4 CBAR s for wake surfaces PANAIR Structured Grids Plume base e Similar to structural FEM MSC NASTRAN the entire configuration is defined by grids
360. scribed in the remarks of the SPLINE3 bulk data card the structural points used by the TPS method can not be located close to or within the same plane Otherwise an ill conditioned spline matrix may result For such a case where the wing like component thickness is very thin the IPS method is recommended but only with the selection of either the upper skin or the lower skin grid points 6 2 MODELING GUIDELINES OF SPLINE FOR FLEXIBLE LOADS 6 2 SPLINE FOR DISCONTINUOUS STRUCTURE A typical case of a discontinuous structure is a control surface The control surface creates discontinuous displacements between its side edges and the main wing as well as discontinuous slopes along the hinge line which may have a large impact on the aeroelastic response For this reason it becomes important to accurately transfer these discontinuous displacements and slopes from the finite element grid points to the aerodynamic model Aileron 8 ovo 2 2 Discontinuous Displacement CAERO7 Macroelement b Structural Finite Element Model Figure 6 2 Spline of Discontinuous Structure Due to a Control Surface Figure 6 2 a presents a wing with aileron configuration modeled by a CAERO7 macroelement that includes 12 wing boxes denoted as box through box 12 The shaded area represents the aileron and its corresponding wing boxes are box 9 and box 12 The finite element model shown in Figure 6 2 b consists of 4 plate type elements generated by
361. se region of the body or NRAD leading edge region of the wing Used only for BLUNT YES and for hypersonic aerodynamics NAXIS is the number of panels along the streamwise direction and NRAD is the number of panels along the circumferential direction for Body or spanwise direction for Wing Integer gt 1 RADIUS Radius of the nose or leading edge at NRAD i Real 2 0 0 PANLST Identification number of a PANLST2 bulk data card that lists NAXIS panel identification numbers at NRAD i Integer gt 0 See Remark 2 4 120 BULK DATA DESCRIPTION MATBODY Remark l The MATBODY bulk data card is referred to by the PSHELL bulk data card All panels that refer to the PSHELL bulk data card and the MATBODY bulk data card are grouped into one aerodynamic component In the following example the panels 101 102 104 205 and 1000 are grouped into one aerodynamic component called STORE CQUADA 101 1 E PSHELL 1 10 m CTRIA3 102 1 CQUADA 104 3 CQUADA 205 3 PSHELL 3 10 CQUADA 1000 3 MATBODY 10 STORE TYPE NOSERAD BLUNT NAXIS NRAD RADIUS PANLST are used only for hypersonic aerodynamics NAXIS NRAD RADIUS and PANLST are used only if BLUNT YES The following example shows a sample input of the MATBODY bulk data card for a blunt nose body with nose radius 1 05 RADIUSi 1 05 all 1 ail
362. section click on the Contour button Click on the Deformed and Contour Data button bar the window that opens under Output Vectors Contour select either CP VALUE or LACAL MACH to be displayed Click on OK for both windows NASTRAN Compatible Output The NASTRAN compatible output is saved in standard NASTRAN bulk data format A sample is shown in the following figure and is described below GRID alt 0 0000000 0000000 000000 GRID 2 0 2000000 0000000 092000 GRID 3 0 2000000 0460000 080000 GRID 4 0 2000000 0800000 046000 Aerodynamic GRID 5 0 2000000 0920000 000000 Grid Points GRID 6 0 2000000 080000 0 04600 GRID 7 0 2000000 046000 0 08000 PSHELL 1 1 1 1 1 00 0 CTRIA3 1 1 ali 2 3 CTRIA3 2 1 1 3 4 CQUADA 7 1 2 9 10 3 CQUAD4 8 x 3 10 tt s Quadrilateral CQUAD4 9 1 4 11 12 5 Elements CQUAD4 10 1 5 12 13 6 CQUAD4 11 1 6 13 14 7 PLoT FILES 7 13 PLOAD4 2 12 690 01 PLOAD4 22 867 01 PLOAD4 1 33 232 01 PLOAD4 1 43 735 01 Pressures PLOADA 1 54 271 01 PLOADA 1 64 615 01 The comment title cards list the identification number of the current PLTCP bulk data card Standard PLOAD4 bulk data cards are used for the pressure output The PLOAD4 bulk data card SID entry is used to delineate the real from imaginary components of the pressure The number of aerodynamic grid points GRID quadrilateral CQUAD4 elements and PLOAD4 bulk data cards within the plot file are also
363. specified MAXMOD Note can be used by itself without specifying a MAXMOD entry Integer gt 0 Remarks 1 The OMITMOD bulk data card is not referred to by any other bulk data card Its existence triggers the program to delete some of the modes that are imported by the ASSIGN Executive Control Command It should be noted that the remaining modes are used by the TRIM analysis 4 126 DATA DESCRIPTION OUTPUT4 OUTPUT4 Export a Matrix Data Entity Description Exports a matrix data entity in the OUTPUT4 format to a data file See description of ASSIGN MATRIX Executive Control Command for the definition of the OUTPUT4 format Format and Example 1 2 3 4 5 6 7 8 9 10 Field MATNAM FILENM FORM Remarks Contents The name of the matrix to be exported Character See Remark 1 Character string specifying the name of the data file in which the data of the matrix is stored The file name is always in uppercase In case the input file name is given in lowercase the program converts it to uppercase If the first character of FILENM starts with a dollar sign the rest of the characters must be integers This integer is the identification number of an EXTFILE bulk data card where the filename is specified This feature allows for filenames up to 72 characters to be input Character Character string either FORMAT FORMAT23 or UNFORM For FORM FORMAT
364. sts see Section 2 4 ZONAIR Output Files Additional details relating to these files and details on execution of the ZONAIR software system are described in the following sections AERODYNAMIC INFLUECE COEFFICIENT AIC MATRICEIS Optional for restart capability OUTPUT FILE myjob out INPUT FILE myjob inp FEM OUTPUT FILE SOFTWARE LOGFILE Free vibration solution myjob log NASTRAN ASTROS I DEAS or Free Format 2 SYSTEM DynamicFix Pathname where run time PLOT FILES database files are executed Aerodynamic model Unsteady pressure Flutter mode shapes T Interpolated mode shapes ZONA License RUN TIME DATABASE Server ZLS 7 Dp Da Files token Deleted Upon Termination Figure 2 1 The ZONAIR Software System File Processing 2 2 HowTo RUN ZONAIR 2 2 INPUT FILES The ZONAIR input file is made up of three sections that describe the aeroelastic problem to be analyzed These are the following Executive Control Section 2 Case Control Section 3 Bulk Data Section Figure 2 2 shows the ZONAIR input data structure format Leading comments initiated with a are allowed Executive Control Section ASSIGN FEM filename FORM form BOUNDARY type PRINT print DIAG values CEND Case Control Section TITLE title ECHO sort nosort SUBCASE
365. symmetric ASYM asymmetric ACTID Not Used COEFFi A list of coefficients to define the linear combination of a set of AESURFZ bulk data cards Real See Remark 3 AESURFi list of LABEL entries defined in the AESURFZ bulk data cards Character Remarks 1 AESLINK provides a means to handle more than one aerodynamic control surface that is driven by one actuator or one control input command Among all AESLINK AESURFZ PZTMODE GRIDFRC and JETFRC no duplicated LABEL is allowed 2 TYPE must match the TYPE entry defined in the AESURFZ bulk data cards that are specified in the AESUREF list 3 Theresulting aerodynamic forces moments of AESLINK is gt Coeffi 9 where is the aerodynamic forces moments of AESLINK is the aerodynamic forces moments of the i AESURFZ 4 24 BULK DATA DESCRIPTION AESURFZ AESURFZ Control Surface Definition Description Specifies an aerodynamic control surface Format and Example i 2 3 4 5 6 7 8 9 10 AESURFZ LABEL TYPE CID SETK SETG ACTID AESURFZ RUDDER ASYM 1 10 Field Contents LABEL Unique alphanumeric string of up to eight characters used to identify the control surface Character See Remark 2 TYPE Type of surface Character SYM symmetric surface ANTI anti symmetric surface ASYM asymmetric surface CID The absolute value of CID is the identification number of a rectangular coordinate
366. system CORD2R bulk data card For CDI 0 Y axis of this coordinate system defines the hinge line of the control surface For CID 0 the Z axis of the coordinate system defines the hinge line of the control surface Integer or blank See Remark 3 SETK Identification number of PANLST1 PANLST2 or PANLST3 bulk data card used to identify the aerodynamic panel ID s of the control surface Integer gt 0 SETG Not used ACTID Not used Remarks 1 existence of an AESURFZ bulk data card triggers the program to generate the aerodynamic forces and moments due to the control surface deflection The user can activate the PLTSURF bulk data card to view the deflected control surface 2 The LABEL is arbitrary but all labels must be unique 3 The y axis or z axis of the rectangular coordinate system should pass through the hinge line of the control surface The rotation about the y axis or z axis by the right hand rule defines the direction of the control surface deflection For instance the figure shown below indicates that the positive deflection of the control surface is deflecting downward BULK DATA DESCRIPTION 4 25 AESURFZ CID lt 0 If CID 0 then the y axis of the basic coordinates is used to define the hinge line location Note that if the control surface consists of CQUAD4 CTRIA3 panels not the CAERO7 panels the x axis of the rectangular coordinates must be towards downstream so that t
367. t be an integer 0 FORM Form of matrix as follows Integer 2 General rectangular matrix 6 Symmetric matrix TIN Type of matrix being inputted as follows Integer 1 Real single precision one field used element 2 Real double precision one field used element 3 Complex single precision two fields used element 4 Complex double precision two fields used element TOUT Not used LARGE Character string either or DMIS Character See Remark 2 LARGE DMIL the element of the matrix is defined by the bulk data card LARGE DMIS element of the matrix is defined by the DMIS bulk data card M Number of rows in NAME Integer gt 0 N Number of columns in NAME Integer gt 0 Remarks 1 The name of the matrix cannot be the same as the name of any data entities existed on the runtime database 2 DMIL bulk data card is the large field matrix input 1f high precision is required for defining the numerical values of the matrix elements Otherwise use DMIS bulk data card BULK DATA DESCRIPTION 4 71 DMIG DMIG Direct Matrix Input at Structural Finite Element Grid Points Description Defines structure related direct input matrices with terms located by specifying the identification numbers of the structural Finite Element Method FEM grid points and their component values Format and Example NAME PREC FORM GCOL CCOL GROW CROW X
368. t file and the FEM output file reside type the following command zonair inputfilename lt outputfilename gt where outputfilename is optional An example is shown as follows zonair myjob xxx myjob out output files will be placed in the same directory where the job was submitted after the program terminates See Section 2 6 The ZONAIR Script File for a detailed description of this process that takes place during code execution How TORUNZONAIR 2 1 21 INPUT AND OUTPUT FILES ZONAIR Figure 2 1 shows the ZONAIR software system file processing that occurs during program execution Four files are required to run the code namely the input file which contains the executive control case control and Bulk Data Sections that describe the aerodynamic model flight conditions etc the structural Finite Element Method FEM output file containing the structure natural frequencies and mode shapes DIRNAME FIX which contains the pathname where the ZONAIR run time database files are to be located LICENSE DAT which contains the user authorization codes required to run the ZONAIR program and ZONAIR DBS which contains permanent database information A minimum of two output files are generated for each ZONAIR run These are the output file of the job and the logfile which contains the elapsed and step CPU times for each module call during the execution of ZONAIR Additional output plot files can be generated through bulk data input reque
369. t that is modeled by a set of GRID CQUADA CTRIA3 and CBAR bulk data cards whereas the CAERO7 bulk data card generates a sheet of vortex and source singularities distributed on the main plane of the thin wing All coordinate locations defined above in XRL ZRL XTL YTL and ZTL are in the local wing coordinate system defined by the ACOORD bulk data card The thick wing component has NCHORD 1 chordwise strips and NSPAN 1 spanwise strips of the panels on the upper surface and the lower surface of the thick wing component respectively Two sets of NCHORDXNSPAN surface grid points are automatically generated by the THKWING bulk data card The first set of grid points 1s on the upper surface and the second set on the lower surface of the thick wing component The starting identification number of those grid points is defined by WID and the identification number of the last grid points is WID 1 2xNCHORDXNSPAN The user must make sure that no duplicate identification numbers exist between those automatically generated grid points and other grid points defined by the GRID bulk data card Likewise 2x NCHORD 1 x NSPAN 1 CQUAD4 CTRIA3 elements are also automatically generated with starting identification numbers being WID duplicated identification number is allowed between those automatically generated CQUAD4 CTRIA3 elements and those defined by the CQUAD4 CTRIA3 bulk data cards See the following figure as an example 4
370. t trim variable whereas the trim variables whose identification numbers are listed in IDVAR entries of the TRIMLNK bulk data cards are called dependent trim variables The TRIMLNK bulk data card provides a feature that allows the user to establish a linear relationship between the dependent trim variables and the independent trim variable For instance the deflections of the leading edge and trailing edge flaps of fighters are often scheduled according to the angle of attack for optimum lift to drag ratio To model such a so called flap scheduling control surfaces the user can specify ALPHA to be the independent trim variable and the leading and trailing edge flaps as the dependent trim variables 2 Thetype of aerodynamic stability derivative generated by both independent and dependent trim variables must be the same Thus the SYM entry in the TRIMLNK bulk data card serves as input error detector If the SYM entry is different from the SYM entries specified in the TRIMVAR bulk data cards a fatal error occurs 4 192 DATA DESCRIPTION TRIMLNK 3 The resulting aerodynamic stability derivatives of the variable linked trim variable are computed based on the following equation Aerodynamic Stability Aerodynamic Stability Resulting Aerodynamic Derivatives of the Derivatives of the M LN Coeff ie Stability Derivatives Independent i 1 Dependent Trim Variable Trim Variable BULK DATA DESCRIPTION 4 193 TRI
371. te Ret b eth edd 1 1 1 1 WHAT IS ZONATR der 1 1 1 2 FINITE ELEMENT BASED HIGH ORDER PANELING SCHEME eee eene 1 2 1 3 NO REQUIREMENT FOR MODELING WAKE SURFACES ccccsessscecececsessnsececececsensnssceeececeeneas 1 3 1 4 NASTRAN BULK DATA INPUT FOR ZONAIR eee en nennen 1 3 1 5 DIRECT ADOPTION OF OFF THE SHELF FEM PRE PROCESSOR FOR PANEL MODEL 25 ce ete oret te reed ee 1 4 1 6 VALIDATION CASES FOR ZONAIR AERODYNAMICS 1 5 1 7 SPLINE MOD U EE referee ree eec ree 1 11 1 8 STATIC AEROELASTIC TRIM 8 ese se sess es es esee 1 11 1 9 PRESSURE INTERPOLATION SCHEME FOR FLEXIBLE LOADS IN TRANSONIC FLOW 1 12 1 10 AIC CORRECTION MODULE FOR ACCURATE FLEXIBLE LOADS 1 13 2 0 HOW TO RUN ZONAIR teet e e e Pete ete E ERE 2 1 24 INPUT AND OUTPUT FILES OF ZONAIR 222000000 0 0 000 2 2 2 2 INPUTEBILES uineis deiude dedere BE 2 3 2 3 RUN TIME DATABASE aene er 2 4 2 4 OUTPUTEIEES AEA BERR RAE RE EEE 2 4 2 5 ZONAIR RESTART CAPABILITY nnn n nnn nennen na 2 7 2 6 ZONAIR SCRIPT FIEE iet ee 2 7 2 7 THE ZONA LICENSE SERVER 71 5 1 212 2 2 0000000000000 000000000000 nennen innen 2 10 2
372. ted an inviscid vortex flow at which the induced velocity is infinite at the center of the vortex core This may create numerical problems if a receiving point exactly aligns with the line of the CROD To circumvent this problem the user may select the viscous vortex core model by specifying the VISCOUS bulk data card 4 72 BULK DATA DESCRIPTION CSHEAR CSHEAR Wake Panel Description Defines a wake panel on the curved wake surface Format and Example i 2 3 4 5 6 7 8 9 10 CSHEAR EID PID G1 G2 G3 G4 CROD CBAR CSHEAR 10 20 101 131 140 160 13 2 Field Contents EID Unique identification number Integer gt 0 See Remark 1 PID Identification number of a PSHEAR bulk data card Integer gt 0 See Remark 2 G1 G2 G3 Identification numbers of the surface grid or reference grid points that connect the and G4 CSHEAR panel Integer gt 0 See Remark 3 CROD Indices of the four side edges of the CSHEAR panel along which CROD elements are attached Integer or Blank CBAR Same as CROD but for the CBAR elements Integer of Blank See Remark 4 Remarks l To model a curved wake surface shed from a body or thick wing component the user can discretize the curved wake surface by reference grids defined by the GRID bulk data card with entry PS40 and connect these reference grids by the CSHEAR panels In the following example the curved wake surface that is attached t
373. ted in the negative Y axis Integer default 0 See Remark 2 Identification number of an OMITCFD bulk data that defines the CFD surface mesh index Integer gt 0 See Remark 3 Character sting to specify the format of the CFD mesh and solution The INPCFD bulk data card reads in the CFD mesh and solution in the PLOT3D format Because there are various options of the PLOT3D format the format of the CFD file must be one of the characters shown in the following table For Formatted Solution Formatted Normalized Without With for IBLANK IBLANK p 1 0 P3D IP3D 10 P3DI IP3DI p 1 0 P3D2 IP3D2 P 10 p 1 0 P3D3 IP3D3 y 1 0 4 100 BULK DATA DESCRIPTION INPCFD For Unformatted Unformatted Solution Single Precision Double Precision Normalized Little endian Big endian Little endian Big endian for Without With Without With Without With Without With IBLANK IBLANK IBLANK IBLANK IBLANK IBLANK IBLANK IBLANK 1 0 UP3D IUP3D UP3DB IUP3DB UDP3D IUDP3D UDP3DB IUDP3DB or or or or or or or or 1 0 UP3DI IUP3DI UP3DBI IUP3DBI UDP3DI IUDP3DI UDP3DBI IUDP3DBI p 1 0 P 10 UP3D2 IUP3D2 UP3DB2 IUP3DB2 UDP3D2 IUDP3D2 UDP3DB2 IUDP3DB2 1 0 y 10 UP3D3 IUP3D3 UP3DB3 IUP3DB3 UDP3D3 IUDP3D3 UDP3DB3 IUDP3DB3 For Binary Binary Solution Single Precision Double Precision Normalized Little endian Big end
374. the bulk data card Fields two through nine contain data input information for the bulk data entry The tenth field never contains data it is reserved for a continuation card if applicable Two types of format are allowed for each bulk data card the fixed format and free format Fixed Format Fixed format separates a bulk data card into ten equal fields of eight columns each 8 columns 1 2 3 4 5 6 7 8 9 10 96 80 columns j BULK DATA DESCRIPTION 4 1 A typical bulk data card is shown as follows 1 2 3 4 5 6 7 8 9 10 PANLST1 SETID MACROID BOX1 BOX2 name of entries not used Field 10 is used only for the Bulk Data Card d optional continuation information Example PANLST1 100 111 111 118 The name of the bulk data card must appear in the first field and start from the first column Three possible types of data can be specified for bulk data entries and are described as follows Integer numerical value with no decimal point Real numerical value with a decimal point Character can be any alphanumeric string Real numbers may be specified in various way The following examples are all acceptable 3 14 3 14 00 314 01 314 1 314 1 31 4 01 The above example shows that each bulk data card allows 8 entries to be specified from field 2 to
375. the aerodynamic pressure coefficients forces and moments the AEROGEN bulk data card also computes the sectional loads defined by all the LOADMOD bulk data cards specified in the Bulk Data Section The non dimensional roll pitch and yaw rates are defined as PRATE roll rate REFB 2 0 V QRATE pitch rate REFC 2 0 V RRATE yaw rate s REFB 2 0 V where V is the free stream velocity which is not required for input The quantities REFB and REFC are the reference span and reference chord respectively specified in the AEROZ bulk data card with units specified in the FMLUNIT entry Computing aerodynamic stability derivatives requires the assembling of an Aerodynamic Influence Coefficient Matrix AIC whose computational time may not be small These aerodynamic stability derivatives are the derivatives of the drag side force lift roll moment pitch moment and yaw moment with respect to a D p q r and the aerodynamic control surfaces including all AESURFZ AESLINK PZTMODE and JETFRC bulk data cards The AIC matrix for computing the aerodynamic stability derivatives can be saved or retrieved using the AJJSAV bulk data card For the AESURFZ or AESLINK bulk data card VALUE is the deflection angle of the control surface in degrees For the PZTMODE or JETFRC the unit of VALUE is defined by the user BULK DATA DESCRIPTION 4 21 AEROZ AEROZ Description Model Physical Data Defines the basic aerodynamic refe
376. the filename is specified This feature allows for filenames up to 72 characters to be input character AERONM The name of a data file in which the aerodynamic model is stored in PATRAN neutral file ONLY USED IF FORM PATRAN Character Default AEROGEOM PAT See Remark 4 BULK DATA DESCRIPTION 4 141 PLTCP Remarks 1 IDPLT is not referred to by other bulk data cards The existence of each PLTCP the bulk data input triggers the generation of a data file for the purpose of plotting the aerodynamic results IDPLT is used for error message output only 2 aerodynamic results generated by the AEROGEN include pressure coefficients and local Mach numbers 3 format of the data file is defined by the entry FORM data of the aerodynamic model together with the aerodynamic results are stored in the data file FILENM Using the TECPLOT M or PATRANTM software depends on FORM TECPLOT or FORM these aerodynamic results of each aerodynamic panel can be displayed on the aerodynamic model 4 PATRAN requires that the aerodynamic model be stored in a neutral file and that analysis results be stored in a results file Therefore the AERONM entry is used to assign a name for a neutral file that contains the aerodynamic model while the FILENM entry specifies a file that will contain the aerodynamic results 4 142 DATA DESCRIPTION PLTMODE PLTMODE ASCII Text Fil
377. the mode that is used to generate the given component forces moments Character default RIGID See Remark 2 TYPE FEM The structural finite element modes that are imported by the ASSIGN FEM Executive Control Command AESURFZ The control surface modes that are defined by the AESURFZ AESLINK PZTMODE or GRIDFRC bulk data cards TYPE LOADMOD load modes that are defined by the LOADMOD bulk data cards TYPE RIGID For rigid body modes LABEL Defines the index of the modes For TYPE FEM If LABEL is an integer LABEL represents the index of the structural finite element modes Integer gt 0 For TYPE AESURFZ LABEL represents the LABEL entry of the AESURFZ AESLINK or PZTMODE bulk data cards Character For TYPE LOADMOD If LABEL is an integer LABEL represents the identification number of the LOADMOD bulk data cards Integer gt 0 BULK DATA DESCRIPTION 4 217 WTIFRC LOADMOD DYNP Al RFORCEI IFORCEI 2 RFORCE2 IFORCB2 Remarks For TYPE RIGID LABEL is a character string and must be one of the following For SYM SYM LABEL FORAFT Represents the for aft translational mode LABEL PLUNGE Represents the plunging mode and LABEL PITCH Represents the pitching mode For SYM ANTI LABEL YTRANS Represents the y translational mode LABEL YAW Represents the yawing mode and LABEL
378. ty derivative SYM ASYM for both longitudinal and lateral stability derivatives INITIAL Initial guess of the trim variable for the minimization computation of an over determined trim system Real BULK DATA DESCRIPTION 4 197 TRIMVAR DCD DCY DCL DCR DCM DCN Remarks User input aerodynamic stability derivatives of the rigid aircraft Character or Real default See Remark 7 Two options are available Character NONE use program computed value Real Value user input value to replace the program computed value 1 is referred to by the IDVARI entry in the TRIM bulk data card 2 There are three types of trim variable 4 198 The Program Assigned Trim Variables The program assigned trim variables are those variables whose aerodynamic stability derivatives and the derivatives of the distributed aerodynamic pressures are computed internally by the program Each program assigned trim variable has a hot wired label If the character string specified in the LABEL entry matches the hot wired label the program internally computed aerodynamic stability derivatives are used for solving the trim system These program assigned trim variables are listed as follows Hot Wired Description Unit Type of Aerodynamic Stability Label Derivatives ALPHA Angle of Attack degree Longitudinal Stability Derivative BETA Side Slip Angle degree Lateral Stability Derivati
379. ults are saved in two separate files The aerodynamic model is saved in the neutral file format while the pressure and local Mach number results are saved in a results file Both files will need to be imported into PATRAN to display the results A sample of the PATRAN compatible output files are shown in the following figures and are described below 7 8 PLorFiLES Neutral File of the Aerodynamic Model 25 0 0 1 0 0 0 0 0 ZONAIR AERODYNAMIC MODEL PATRAN NEUTRAL FILE OUTPUT 26 0 0 1 91 65 1 1 0 08 22 200016 11 23 2 5 1 201 0 2 0 0 0 0 0 0 100000000E 03 0 000000000E 00 0 000000000E 00 0G 6 0 0000000 1 202 0 2 0 0 0 0 0 0 100000000E 03 0 000000000E 00 0 000000000E 00 0G 6 0 0000000 TUM Aerodynamic Grid Points 2 201 4 2 0 0 0 0 0 4 0 1 0 0 000000000E 00 0 000000000E 00 0 000000000E 00 202 207 206 201 2 202 4 2 0 0 0 0 0 4 0 1 0 0 000000000E 00 0 000000000E 00 0 000000000E 00 203 208 207 202 LN Aerodynamic Panels Data Packets 1 Node Data and 2 Element Data are used to output the aerodynamic grid points and aerodynamic panels respectively Results File of the Pressure Element Results ZONAIR STEADY CP AND MACH NU 1 FLEX NO M 0 60 0 00 2 RESULT QUANTITIES MACH NUMBER 1 3 0 2690387E 000 5080803E 00 2 3 0 2867234E 000 5015833E 00 3 3 0 3232428E 000 4879461E 00 4 C 0 3735698 000 4686236 00 5 3 0 4271863E 000 4472803E 00 6 a 0 4615177E 000 4331503E 00 The Element
380. um center Z location of the momentum center Number of control surfaces Length unit of the aerodynamic model Mass unit of the aerodynamic model The values of REFC REFB REFS REFX REFY REFZ No AESURFZ LENGTH UNIT and MASS UNIT respectively that are specified by the AEROZ bulk data card Real Format 6E12 4 I12 2A12 Character string where MACH Mach number H Altitude with unit LENGTH UNIT ALPHA Angle of attach in degree BETA Side slip angle in degree PRATE Non dimensional roll rate PRATE PB 2V Where p is the roll rate in rad sec b is the reference span REFB and V is the freestream velocity ORATE Non dimensional pitch rate QRATE qc 2V Where q is the pitch rate in rad sec c is the reference chord REFC RRATE Non dimensional yaw rate RRATE rb 2V Where r is the yaw rate in rad sec Cp Drag Coefficient Cp D D is the drag force 4 REFS Cy Side Force Coefficient Cy Y Y is the side force qoo REFS Ci Lift Coefficient CL L L is the lift force Goo REFS CR Roll Moment Coefficient C t is the roll moment qe REFS REFB CM Pitch Moment Coefficient Cu M M is the pitch moment qo 8 CN Yaw Moment Coefficient Cy N N is the yaw moment oo REFS REFB 4 04 DATA DESCRIPTION GENBASE FILEi Card 6 Character string up to 12 characters that is that file name on which the aerodynamic data of each panel is stored This file conta
381. umber of a bulk data card that defines the objective function to be minimized Active only for an over determined trim system Integer 2 0 IDCONS Identification number of a TRIMCON bulk data card that defines set of constraint functions to be satisfied Active only for an over determined trim system Integer 2 0 RHOX RHOY X y and z components respectively of a vector from the aerodynamic moment center RHOZ REFX REFY and REFZ in the AEROZ bulk data card to the center of gravity C G of the configuration Thus the center of gravity is computed by REFX RHOX REFY RHOY zco RHOZ Real 4 178 DATA DESCRIPTION TRIM WTMASS WEIGHT IXX IXY IYY IXZ IYZ IZZ TRNACC NX NY NZ PDOT QDOT RDOT LOADSET IDVARi VALi Factor to convert weight to mass WTMASS 1 0 where gis the gravitational acceleration Real gt 0 0 The weight of the whole aircraft Real gt 0 0 See Remark 4 The weight moment of inertia about the center of gravity C G of the whole aircraft where the x y and z denote the rotational axis that are associated with the aerodynamic model Real See Remark 4 Note IXX IYY and IZZ must be greater than zero Character string to specify the units of the accelerations NX NY NZ PDOT QDOT and RDOT of the trim degrees of freedom Character Default TRNACC TRUE The units of the acceleratio
382. ust be operational 2 7 7 71 5 ERROR CODES The following is a list of the ZLS status and error codes last one or last three digits that are reported in the ZONAIR output file or are displayed on the screen in the event of an error during submission and execution of a ZONAIR job If the encountered error cannot be resolved please contact ZONA s technical support staff for assistance Section 7 1 of ZONA License Server User s Manual documents the error codes in more detail ZLS STATUS ERROR CODES RELATED TO ZONAIR 0 Success status the operation succeeded with no warnings Related to direct interaction with zls server 101 Exception occurred at opening socket Don t know about host provided 215 102 Exception occurred at opening socket Couldn t get I O connecting to provided zlsIP 103 Exception occurred at fillarray 104 Exception occurred at readLine Be aware zls server might be forced down Related to license file 201 License has expired 202 License product name check failed at reading license Related to software product operation 601 Needed module was not found in license 602 Needed module was not available 603 CheckoutID was not found in the record 604 Module inconsistency was found in the license 605 Token count inconsistency was found in the license 2 12 HowTo RUN ZONAIR Chapter 3 EXECUTIVE CONTROL AND CASE CONTROL SECTIONS The Executive Control Section must be located at the beg
383. ut blade sting H 18 without blade sting SS TR RRA 10 7 4 H 17 Blade Sting H 18 Blade Sting H 17 without Blade Sting H 18 without Blade Sting 1 8 INTRODUCTION e Good agreement between ZONAIR and measured wave drag indicates that the incremental wave drag measurements are small Blade Sting Effects on Wave Drag of GAF M 1 2 ZONAIR Wave Drag Predictions blade sting effects on Measured Drag H 17 blade sting H 18 blade sting 33 counts 31 counts H 17 without blade sting H 18 without blade sting 34 counts N A Ground Effects Compact Kinetic Energy Missile CKEM Flying 5 Inches Above the Ground at M 2 0 e Mirror image approach where the ground is treated as a mid plane between two mirror image bodies ZONAIR can compute flow field solutions for the visualization of the detailed flow field solutions e Good agreement of the pressure distribution on the body surface and in the flow field can be seen For this case ZONAIR takes about 10 minutes of CPU time on a 550 MHz PC computer whereas CFL3D takes about 10 hours 0 120853 0 102058 0 0832638 0 0644693 0 0456749 0 0268805 0 00808606 0 0002 0 0107084 0 0295028 ZONAIR CFL3D Pressure Distribution of CKEM Flying 5 Inches Above the Ground at M 2 0 Aeroheating Analysis Afinite element based streamline mo
384. ut format for the steady pressure distribution is identical to the PLTCP bulk data card except that the imaginary component of the pressure result will always be zero while the real component will reflect the steady pressure please see Section 7 2 for a description of this output format 7 20 PLOT FILES e NASTRAN Compatible FORCE MOMENT Output The output format of the ASCII text file containing the NASTRAN FORCE and MOMENT bulk data cards is shown in the following figure 5 5 amp MOMENTS AT FEM GRIDS RESULTING FROM TRIM 100 FOR FLEXIBLE MODEL 5 MACH 0 9000 DYNAMIC PRESSURE 0 12000E 04 5 5 8 MOMENTS IN TERMS OF NASTRAN FORCE AND MOMENT BULK DATA CARDS FOR TWO SIDES OF THE MODEL SWHERE LOAD SET 100 REFERS TO THE GRIDS ON THE RIGHT HAND SIDE OF THE MODEL LOAD SET 101 REFERS TO THE GRIDS ON THE LEFT HAND SIDE OF THE MODEL THE USER CAN INSERT THIS FILE BACK TO THE FEM MODEL FOR SUBSEQUENT STATIC ANALYSIS AND STRESS CALCULATIONS FORCE 00 90 00 000400 000 0 000 0 000 FORCE 00 90 00 000400 0 000 000 0 000 FORCE 00 90 01 665404 0 000 0 000 000 MOMENT 00 90 04 083404 000 0 000 0 000 MOMENT 00 90 04 859404 0 000 000 0 000 MOMENT 00 90 00 000400 0 000 0 000 000 FORCE 00 97 0 2 93 10 000 0 000 0 000 FORCE 00 97 O23 39 173 0 000 000 0 000 FORCE 00 97 0 7 20 03 0 000 0 000 000 00 97 00 000 00 000 0 000 0 000 MOMENT 00 9T 00 000400 0 000 000 0 000 MOMENT 00 97 00 000 00 0 00
385. ution simulation Trim analysis ZONAIR Off the shelf 3 0 Spline PATRAN ZONAIR Panel Model I DEAS generation Automated Mesh Generation AEROLAB Figure 1 1 Interrelationship of ZONAIR with Other Engineering Software Systems Aerodynamic and loads database Aerodynamic force moment generation Critical loads identification Pressure mapping Wind Tunnel measured loads for AIC correction CFD Result INTRODUCTION 1 1 1 2 FINITE ELEMENT BASED ORDER PANELING SCHEME The ZONAIR panel model is normally constructed by first descretizing the configuration into many grid points and then connecting these grid points with either the quadrilateral or triangular panels This type of panel construction is very similar to the structural finite element method In fact some of the NASTRAN bulk data cards are directly adopted for ZONAIR input In order to ensure the continuity of singularity distribution over the entire panel model unit singularity strength is first assigned at each grid point and piecewisely linear singularity is distributed over the panels which are surrounding this grid Such an elementary singularity distribution is shown in Figure 1 2 Clearly the superposition of the elementary singularity distribution of all grid points can result in a continuous singularity distribution over all panels
386. utput is saved in the FEMAP ver 7 0 neutral file format Data Blocks 403 and 404 are used to output the aerodynamic grids and panels respectively Data Block 450 is used to output the flutter mode output set definition Data Block 451 is used to output four data vectors to display the interpolated mode shape TOTAL Translation X axis translation T1 Y axis translation T2 and Z axis translation T3 A sample of the FEMAP compatible output is shown in the following figure 1 100 Neutral File Header NUDES s followed by other 1 required Data Blocks 1 403 201 0 0 1 46 0 0 0 0 0 0 1 0000000000000000D 02 0 0000000000000000D 00 0 0000000000000000 00 202 0 0 1 46 0 0 0 0 0 0 1 0000000000000000D 02 0 00000000000000000 00 0 0000000000000000 00 j 203 0 0 i 46 0 0 0 0 0 0 1 0000000000000000D 02 0 00000000000000000 00 0 0000000000000000 00 204 0 0 1 46 0 0 0 0 0 0 1 0000000000000000D 02 0 0000000000000000 00 Grid Points 1 404 201 124 1 17 4 1 0 0 0 0 0 0 202 207 206 201 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0000000000000000D 00 0 00000000000000000 00 0 0000000000000000 00 0 00000000000000000 00 0 00000000000000000 00 0 0000000000000000 00 0 00000000000000000 00 0 00000000000000000 00 0 0000000000000000 00 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 0 Quadrant Elements 1
387. ve PRATE Roll Rate pb 2V Lateral Stability Derivative Pitch Rate qc 2V Longitudinal Stability Derivative RRATE Yaw Rate 1b 2V Lateral Stability Derivative THKCAM Aerodynamic load at the mean None Longitudinal aerodynamic forces Flow Condition defined by the and moments AEROGEN bulk data card If It is recommended that THKCAM INPDMI or INPCFD INPCFD1 always be included for the bulk data card is used to replace symmetric trim system with entry ZONAIR computed pressures VAL 1 0 in the TRIM bulk data with the imported pressures the card loads at the mean flow condition are based on the imported loads where p q and r are the roll rate pitch rate and yaw rate in rad sec respectively about the aerodynamic moment center REFX REFY and REFZ defined in the AEROZ bulk data card b and BULK DATA DESCRIPTION TRIMVAR c are the reference span REFB and reference chord REFC defined in the AEROZ bulk data card V is the free stream velocity and is not required for input The longitudinal aerodynamic stability derivatives are d C d C d trim variable d trim variable d trim variable The lateral aerodynamic stability derivatives are C d Ci d trim variable d trim variable d trim variable where c P D is the drag force d 4 5 c iL L is the lift force L q S C M j M is the pitch moment about REFX REFY and REFZ q Sc ph Beets Y is the
388. ve Control Section Bulk Data Section The last section of any ZONAIR input deck is the Bulk Data Section The BEGIN BULK and ENDDATA are required delimiters This section provides the complete engineering data required to perform the disciplines specified in the Case Control Section This includes the geometry of the aerodynamic model spline instructions for displacement and force transferal between the structural finite element grid points and the aerodynamic boxes flight conditions and other parameters such as reference density lengths etc See Chapter 4 for details of the Bulk Data Section 2 3 RUN TIME DATABASE A ZONAIR run time database is generated for each job that is submitted under the ZONAIR script file The database contains relational unstructured and matrix entities stored in separate scratch files that are created by ZONAIR during execution of the software The location of the run time database is dependent on the pathname specified in the DIRNAME FIX file that is stored in the ZONAIR home directory Temporary database folders under this pathname are created for each job and are removed upon normal termination of the ZONAIR script file The DIRNAME FIX file is setup during initial installation of the ZONAIR software and can be modified by the user to change the location where the ZONAIR database folders are executed Note location specified by DIRNAME FIX should be a very large scratch space with suff
389. wer grid points Note that the out normal vector of those CQUAD4 CTRIA3 elements is defined by the right hand rule from TIPGRID to the grid on the upper surface and then to the grid on the lower surface The AUTOTIP bulk data card automatically generates two sets of CROD elements one is connected by those internally generated upper grid points and the other one is connected by the lower grid points The identification numbers of those internally generated CROD elements start from RODS 4 36 BULK DATA DESCRIPTION AUTOTIP In the example shown above eight CROD elements are automatically generated by the AUTOTIP bulk data card If RODS 1 the identification numbers of those CROD elements 1 8 where CROD 1 4 are connected by the upper grid points and 5 8 by the lower grid points TIPGRID must be an existing surface grid points which is located at the leading edge of the wing tip See the example shown below TIPGRID In the example shown below the surface grid points located along the upper surface of the wing tip are 1003 105 2007 and 2009 whereas the surface grid points located along the lower surface are 2100 1004 1007 and 1002 Note that the surface grid point TIPGRID must be excluded from the lists In addition the x locations of those grid points must be in the ascending order i e from upstream to downstream 1002 1007 1004 2100 For a symmetric aerodynamic model
390. y allocation history This will generate massive output due to the large number of memory calls K 3 Turn on the database file manager debugger 3 28 EXECUTIVE CONTROL SECTION DOUBLE DOUBLE Convert from Single Precision to Double Precision Computation Description Convert the entire computation of the program from single precision to double precision on 32 bit computers Format DOUBLE Example 1 DOUBLE Remarks 1l The DOUBLE command is optional 2 This command also converts all matrix entities stored on the runtime database from single precision to double precision Note that the specification of the DOUBLE Executive Control Command is highly recommended in the case where the stiffness matrix such as the KGG matrix KGG matrix is defined as the G set stiffness matrix is imported by the ASSIGN MATRIX Executive Control Command or the DMI DMIG bulk data card This is because the KGG matrix normally requires high precision to store it On a 32 bit computer the single precision computation without the DOUBLE Executive Control Command involving the KGG matrix will yield large errors due to the truncation error EXECUTIVE CONTROL SECTION 3 29 FLEXLD FLEXLD Invokes the Flexible Loads Analysis Description Invokes the aerodynamic analysis on flexible aircraft by referring to an identification number of the FLEXLD bulk data card The Executive Control Commands ASSIGN FEM SOL 1 are requir
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