AEDsys Program User Guide
Contents
1. Pid Max Oo 9600 Pi b 3500 m Pi tH 0 4231 Pin 3700 Gas Type MSH Equilibrium model Di n n send Tau tH 0 835381 Eta b 3990 Number of Engines E Eta AB 0 9900 Eta 9950 Eta Oo 3950 Eta 0000 Engine Controls Eta 1 0000 Eta f 8674 Max Temperature at Station 4 R Eta 0 8674 Eta cH 5751 Max Compressor Pressure Ratio EH io NE es eem Max Pressure at Station 3 sla ae Rees eae Mas T Station 3 d CP c 0 2400 amma c 4000 as PEIRETO at station CP t 9 7950 aire E 3000 Max Ref RPM LP Spool CP AB 0 23950 Gamma AB 1 3000 Max Ref RPM HF Spool Bleed amp oo1 o00 PiM Max 0 9700 Max Temperature at Station R Cool 1 4 005 00 Cool amp 005 00 PTOL Kil noon i PTOH Rit OS00 6 m Installation Loss Model FARAMETER REFERENCE M 1 4510 le E Constant Loss For Each Leg 0 05 TO im 390 5 C Loss Model of Chapter 6 ae aes aur Inlet Capture Area Al ft bl Lon Afterbady Area A10 t 2 Te iR Enn Afterbody Length L ft ME Oo 4000 Aus Inlet Area t 2 Pi d 0 59354 Mas Mach for Aus Inlet Pi f 3 9 Tau 1 54792 Fi cL ro Component Interfaces Scale Thrust SEEN Thrust Scale Factor Pa 1 0000 As shown below the user is asked if they would like to update the maximum engine temperature s T and Ta in each mission leg with the value s contained in the engine reference file If either the maximum temperature at station 4 or the maximum temperature at station 7 is changed in the above window2. Results Im x LEDevs Ver 3 1 Turbofan with AB Dual Spool Date Engine File C Program FilesVWVAEDzysMA AF Final Engine ref Input Constants Pidmax 0 9600 Fi b 0 9500 Eta b 0 9990 Pin 0 9700 cp c O 2400 cp t 0 25950 Gam c 1 4000 Gam t 1 3000 Fi AB 0 9500 Eta AB 0 9900 cp AB 0 2950 Gam AB 1 3000 Eta cL 0 8693 Eta cH 0 8678 Eta tH O 39028 Eta tL 0 3057 Eta mL 0 929950 Eta mH 0 9950 Eta PL 1 0000 Eta FH 1 0000 Eta f 0 89693 FTO L O 0KRW FTO H 150 0KRW hPER 168400 Bleed 1 00 Cool l 5 00 Cool 5 00 Control Limits Tt4 3200 0 Pic 8 00 Thrust Scale Factor 1 0000 Parameter Beference Test Mach Humber O 1 4510 0 0100 Temperature QO 330 50 5128 53 Prezzure a D 3 3063 14 6960 Altitude a s6000 Total Temp 34 3200 00 2995 53 Total Temp 7 3600 00 3600 00 Pir Taur 3 4211 1 4211 1 0001 1 0000 Pi d 0 9354 O 3600 Pi f Tau f 3 50007 1 4951 3 45987 1 4950 Pi cL Tau cL 3 5000 1 4951 3 49295 1 4950 Pi cH Tau cH 2 00007 1 9351 S 0052 1 9355 Tau ml 0 98623 0 9693 Pi tH 7 Tau tH 0 30837 O 7853 0 30837 0 7953 Tau mz 0 977z 0 297727 Pi tL y Tau tL O 4236 0 8366 0 42357 0 5366 Control Limit FIC Max LP Spool BEM i of Design Pt 100 00 96 68 Press the Engine Station button on the Engine Test window to display a sketch of the engine showing engine station numbers as shown below Res Station Numbers bleed air i 3 3 1 23 Afte
3. 70929 0 69868 446 13096 47060 EIS 4 55 2 95 0 91453 0 655568 0 638356 2508 21067 1067 364 3 25 45 ge 0 99627 0 635356 0 63658 luu 11114 ZO7e4 a7 4 5 4z 10 11 0 93975 0 63658 0 598523 1611 2e7o 2e7O 2 054 4 294 58 16 Pressing the Plot button at the bottom of the Mission window opens the Mission Plots window The user selects the plot at the bottom of this window and presses the Plot button to obtain a plot like that shown below with a bar chart based on the mission leg number wi Mission Plots Mission Results by Leg File C Program Files amp ED sys AED vs AED Date Weight Fraction Beta 1 Beta dv Weight Fraction Beta Time E Cumulative Time C Leg Weight Ratio Pi C Distance 7 Cumulative Distance 17 6 ENGINE CYCLE DESIGN PROGRAMS and DESIGN STEPS ONX Parametric Engine Analysis determines the change in an engine s uninstalled performance with changes in the engine design parameters a design parameter like compressor pressure ratio Can calculate the performance of a reference engine each design parameter set to one design value and output a reference data file REF AEDsys Performs constraint analysis contour plots mission analysis and engine test can input reference data from ONX program and fly this engine through the mission run engine performance calculations variation in an engine s uninstalled performance with changes in engine flight conditions altitude and Mach nu
4. FIC Max 13624 1 3176 142 36 148 28 3 500 29 54 8 005 2383 3 2741 5 AB On PIC Max 13306 1 2647 142 36 148 28 3 500 29 54 8 005 2383 3 2624 8 AB On PIC Max 12990 1 2122 142 36 148 28 3 500 29 54 8 006 2383 3 2510 4 AB On PIC Max 12673 1 1601 142 36 148 28 3 500 29 54 8 005 2383 3 2397 9 AB On PIC Max 12357 1 1082 142 36 148 28 3 500 29 54 68 005 2383 3 2287 5 AB On PIC Max 12039 1 0564 142 36 148 28 3 500 29 54 8 005 2383 3 2178 6 AB On FIC Max 11722 1 0050 142 36 148 28 3 500 29 54 68 006 2383 3 2072 1 AB On FIC Max 11406 0 9538 142 36 148 28 3 500 29 54 8 006 2383 3 1957 8 AB On PIC Max 11089 0 9028 142 36 148 28 3 500 29 54 8 005 2383 3 1855 7 AB Un PIC Max 10773 0 68520 142 36 148 28 3 500 29 54 68 006 2383 3 1765 9 AB Un PIC Max 10455 0 6012 142 36 148 28 3 500 29 54 68 006 2383 3 1668 0 AB On PIC Max 10138 0 7506 142 36 148 28 3 500 29 54 8 005 2383 3 1572 8 AB On PIC Max 9822 0 7002 142 36 145 48 3 500 29 54 6 005 2383 3 1480 0 AB On PIC Max 9502 0 6602 140 71 146 56 3 450 29 45 7 969 2951 8 1437 5 AB Off Thrust Drag 9168 0 6761 138 22 143 96 3 376 29 30 7 911 2323 1 1420 7 AB Off Thrust Drag 0672 0 6718 135 69 141 33 3 302 29 14 7 852 2895 4 1403 3 AB Off Thrust Drag 0555 0 6675 133 15 138 688 3 227 26 98 7 749 2850 9 1385 5 AB Off Thrust Drag 0239 0 6632 130 59 136 02 3 151 28 81 7 744 2825 5 1367 3 AB Off Thrust Drag 7921 0 65868 126 00 133 33 3 076 29 63 7 667 2789 2 1348 5 AB OfFE Thrust Drag Prnt Once the partial throttle has be
5. I5 1445 3600 7O 7O 7O 45 45 45 45 90 EIN 30 gg 30 ov l7 4s 45 4s 31 au ipsia 14 14 11 dd dd dd dd oes Orie 383 204 53 39 dd 44 dil 27 B36 02 3 935 gaz sz sz 7l 931 331 523 333 154 jaz eet 253 SE B66 T Ri 5138 glz i94 TSO 7S0 750 750 1476 1476 1438 zegd 1325 1760 151 PEL 1406 3457 24 63 52g l 79 73 79 BS 14 14 a7 25 ve as zr eu 53 38 100 OOo Oo oo oo ao H cQuocgrm Date C Program Files AEDzysAAF Final Engine AED C Program Files AEDswys AF Final Engine ref 1 0000 Mach Velocity ft s 0100 Z456 4595 4055 4055 4055 4064 Z296 Z296 0801 0000 0000 6013 4007 3986 4230 S5244 11 2v2 544 544 S44 544 545 545 545 151 eS Z067 1187 S03 535 758 1451 16 0 60 ed ed ed 75 41 41 38 53 7S 71 03 59 16 47 f 16 due e Oooo oO oO fF Se MOF F Area C22 6 T O35 wee 649 340 709 938 e 18 194 677 l44 448 i53 543 719 338 466 Area ft z e 281 001 048 595 451 595 104 092Z 093 e Ooo oO oO oO rF Stu rmn Pood ool l144 448 969 369 451 531 660 I lbf 3s528865 3 15485 3295 12578 Tad 5536 T3331 138593 116855 38345 Bom u p oHm in
6. is selected using the combo box beside Type in the middle left of the window Pressing the down arrow on the right edge of the box displays a list of constraint types for user selection as shown below if needed the user can scroll to the desired constraint Constant Altitude Speed Cruise J Acceleration Time Constant Speed Climb K Takeoff Climb Angle Constant Altitude peed Turn L Carrier Takeott Horizontal Acceleration I Carrier Landing Service Ceiling M Carrier Approach Takeoff No obstacle Takeoff Landing After a new constraint type is selected the user presses the Change button to change the current constraint and the appropriate data list is shown on the right Press the Add button to add a new constraint at the current constraint number Press the Remove button to remove the current constraint The Atmosphere radio buttons allow the user to specify the atmospheric model that is to be used for auto update of the air temperature for new altitude data For flight conditions corresponding to one of these atmospheric models enter the altitude first and then enter the desired temperature After entry of the ranges of wing loading and thrust loading pressing the Calculate button opens the results window with the results for the first constraint as shown below Pressing the Print button at the bottom of the Results window sends a copy of that constraint s results to the printer After at least one con
7. package Plots can be custom tailored and printed Screens can be saved printed by first pressing the Alt and PrtSc buttons at the same time this captures a bit map of the current window onto the clip board start the Paint program and paste the image from the clip board onto the blank screen and then save print the image 2 MAIN WINDOW When the AEDsys program is started the default input data file AEDsys aed is read and the main window is displayed as shown below The pull down menu system and push buttons help navigate the user The pull down menus are shown on the next page AEDsys Main File System Analysis Aircraft Drag Engine Links Units Status File C Program Files 4 E Days AE Days AED Drag 5 Future Fighter Units BE Thrust 2 Low BP Mized Than 46 off TH 1 1 TSFC 2 Low BP Mixed Than Inlet Compressor Turbine Nozzle Atmosphere Gas Tables email EGL Combustion Main Burner Afterburner Calculator Paint TAA i 25 FJ ie Pull down Menus Thrust File Pull down Menu Many of the file pull down menu functions are similar to that of other programs Open Save As Plot Print Buffer Printer Setup Change Pictures Exit Display a dialog window to open AEDsys input files extension aed Display a dialog window to save the current data file as an AEDsys data file The default data file AEDsys aed can be replaced with the current data by saving
8. selected the Mission Window is displayed as shown below ede ol RE ae Mame 1 24 arming Up ee 1 24 Warming Up re Max 30 2 1 26 Takeoff Acceleration rpe E Q 4 1 20 Takeott Rotation Altitude ft 4 230 Acceleration T p 5 23Ea Climb Accel Pt1 emperature Fi E 2 3Eb Climb Accel Pt 2 Time sec f 3Ec Climb ccel Pt 3 Engine 46 120n 0ff B 4 5 Descend and Accel 5 6 Supersonic Cruise Deliver Missilles Bombs B ra 1 5M 5g turns rb 0 95g tums fo Accel from 0 9 to 7 6M 0 9 Supersonic Cruise Marne 1 2 A Warming Lp Change Change Type i wamp xl Wing Loading w5 cA Atmosphere Thrust Loading T w 4 f Standard Hot Day lens Weight Fraction at Start Beta 4 Gross Takeoff weight f 42n C ColdDay Tropical Day summary Thrust 3 SL Static T Wing Area 5 Remove Add 15 Ci J B C C E 3 3 4 Subsonic Cruise C E L F F B E Empty Weight Ib Model User Defined Model The mission of interest can be constructed using the upper portion of this window Double clicking on an item in the upper left window causes the data for that mission leg to be displayed on the right side of the window for editing The mission analysis can model each of the fourteen 14 legs of the textbook The type of mission leg is selected using the combo box beside Type in the middle left of the window Pressing the down arrow on the right edge of
9. the file as AEDsys aed High resolution constraint and contour plots can use significant printer buffer memory while being generated If the user is connected to a printer by a network and not limited by the network setting opening the printer buffer allows the user to select to print the plot generated by the Constraint Window s Plot button and the plot generated by the Contour Plot Data Window s Plot Contour Lines button Display printer setup window Open a dialog window to select and replace current picture jpg or bmp on Main Window Exit program System Analysis Pull down Menu Provides links to the Constraint Analysis Contour Plot and Mission Analysis portions of the program The user can also navigate using the Constraint Analysis Contour Plot and Mission Analysis buttons on the Main Window 4 Aircraft Drag Pull down Menu User can select from seven 7 drag models The first six models correspond to the data in the Aircraft Engine Design Second Edition The Cpmin Variation with Mach number for the first four drag models are as shown in the textbook The program uses the following data for K C n AR and e min LIRE l 0 001 2 Cargo Passenger Tprop high drag 0 03 03 7 075 User selection of User Input Drag Model opens the following Drag Eqn Window that allows input of drag data versus Mach number The maximum number of data points for each of the three drag coefficients is eleven 11 The Mach number
10. 5 060 z524 29 46 419 7195 03 1 0000 zz 5 36 1 108 1 108 17032 2 5 140 45 1 3000 41 090 2170 26 32 716 2059 07 O 6000 1291 58 2 537 e l12z6 17545 53 e 140 45 1 3000 41 090 z170 26 37 077 2113 39 0 4000 866 81 3 407 e lz6 zZl1975 4 16 61 94 1 4000 41 264 858 99 037 077 833 13 0 3940 557 49 0 925 0 575 6012 8 6L e z 39 1 3250 39 537 1644 00 35 310 1773 45 0 4188 839 14 4 4866 2 899 279885 1 AB fuel 6 6582 7 209 05 1 3000 37 617 3600 00 32 070 3469 88 0 5000 1356 39 6 002 4 453 ee ae 4 F Print Calculate 21 8 ENGINE CYCLE DECK MODEL ENGINE TEST WINDOW Pressing the Engine Test button on the AEDsys main window opens the Engine Test window shown below and performance analysis of the reference engine Pressing the Test button causes the performance analysis software to calculate the engine performance at the percent thrust set in the Thrust data field and update results on the right side of the Engine Test window Engine Cycle J urbotan w AB z Thrust 100 Operating Condition Mach number Altitude Thrust uninstalled 15840 Ibf TSFC uninstalled 1 5355 lIbm bf hr Done Mass Flow Hate 14236 lbm sec CT zn m Ci c JS Temperature H Tt4 2463 3 H Tt 3600 0 A AB Un Engine Controls D Lirit PIC Mas Max Temperature at Station 4 2200 A CPR Prs Ptz 20 02 ts 1500 8 H Max Compressor Pressure Fiatio 28 Fan PR 3 500 mdotc t 4 1 Fed Max Pressure at Station 3
11. 6215 Thrust Drag 3150 9 l5 7 5H Drop Weight 34
12. 6271 0 4235 29853 2 862 3 044 PIC Max 0 05 15686 1 7145 142 56 28 02 3 500 0 754 2 9669 0 4235 2964 6 2 89681 3 045 PIC Max 0 10 15540 1 7381 143 19 28 01 5 499 0 754 2 596270 0 4235 29887 2 891 3 049 PIC Max 0 15 15460 1 7594 144 25 28 01 3 498 0 754 3 0076 0 4235 2995 7 2 89881 3 055 PIC Max O 20 15447 1 7785 145 76 28 00 3 495 0 754 3 0441 0 4235 3005 7 2 8681 3 064 PIC Max O 25 15499 1 7954 147 72 28 00 3 4595 0 754 3 0815 O 4234 3018 6 2 861 3 075 PIC Max 0 30 15617 1 8098 150 15 28 00 73 497 0 754 3 1504 0 4234 3034 4 2 8961 3 090 PIC Max 0 35 15799 1 8220 153 06 8 00 3 497 0 754 3 227039 0 4234 3053 1 2 861 3 107 PIC Max O 40 16047 1 5318 156 45 28 00 3 456 0 754 3 3041 0 4234 3074 5 2 861 3 125 PIC Max 0 45 16376 1 8388 160 45 28 03 3 495 0 753 3 4029 0 4233 3100 5 2 8963 3 152 PIC Max 0 50 16752 1 54458 164 686 28 01 3 497 0 753 3 5111 0 4233 3127 4 2 893 3 151 PIC Max 0 55 171898 1 84656 169 84 28 00 3 495 0 753 3 6342 0 42352 3157 4 2 893 3 213 PIC Max O 60 17718 1 8507 175 43 28 00 3 494 0 753 3 7727 O lt 4232 3190 5 2 8963 3 250 PIC Max 0 65 17950 1 5634 179 26 27 40 3 437 0 760 3 8587 O 4244 3700 0 2 545 3 250 Tt4 Max 0 70 18083 1 9796 162 53 6 56 73 357 0 771 3 9274 O 4262 3200 0 2 791 3 307 Tt4 Max 0 75 18247 1 8950 l1856 10 258 71 3 276 O 782 4 0026 0 4262 3z UD 0 2 736 3 338 Tt4 Max 0 80 18443 1 5096 190 00 4 84 03 193 0 794 4 0845 0 4303 3200 0 2 680 3 371 Tt4 Max O 85 18671 1 9234 184 24 23 97 3 109 0 806 4 1737 0 4325 3200 0
13. AE On Date Engine File CAPragram Filesy amp EDieysy amp AF Final Engine ret Hight mouse click For plot properties Legend Alt D ay OOk fe Std 1Ok te Std eUk ite Std 3lkft Std JEkft Std 40k Std Thrust Specific Fuel Consumption 2 bm hrf 08 1 12 Mach at Station 0 Similarly the partial throttle performance of an engine can be calculated and plotted using the lower right of the Engine Test window shown below Press the Partial Throttle button to calculate the uninstalled performance of an engine from 100 down to the minimum thrust entered in the Min Thrust data field minimum value is 10 The results are displayed in a Throttle Hook results window as shown on the next page Throttle Hook AEDsys Version 3 3 Date Engine File C Program Filezgz AEDzvgz AA F Final Engine ref Throttle Hook Mach 0 00 Altitude 0 ft TO 518 67 E Standard Day Thrust S mdot mdotce pif mdotczb5 picH Tt4 Tt AB Limit 158339 1 6954 142 36 148 28 3 500 29 54 8 006 2383 3 3599 6 AB On PIC Max 15525 1 6408 142 36 148 28 3 500 29 54 8 006 2383 3 3473 5 AB On PIC Max 15208 1 5860 142 36 148 28 3 500 29 54 8 005 2383 3 3347 7 AB On PIC Max 14832 1 5318 142 36 148 28 3 500 29 54 8 005 2383 3 3223 6 AB On PIC Max 14574 1 4775 142 36 148 28 3 500 29 54 68 005 2383 3 3100 3 AB On PIC Max 14257 1 4233 142 36 148 28 3 500 29 54 8 005 2383 3 2979 0 AB On PIC Max 13940 1 3705 142 36 148 28 3 500 29 54 8 005 2383 3 2853 3 AB On
14. AEDsys Program User Guide Version 3 1 May 17 2003 Copyright 2002 Jack D Mattingly Ph D COND MN B WN ee Table of Contents General Description of Program Main Window Constraint Analysis Contour Plots Mission Analysis Engine Cycle Deck Design Programs and Design Steps Engine Cycle Deck Model Engine Data Window Engine Cycle Deck Model Engine Test Window Engine Cycle Deck Model Mission Analysis 11 14 18 19 22 31 1 GENERAL DESCRIPTION OF PROGRAM The program AEDsys is based on the design tools in Chapters 2 through 7 of the AIAA Education Series textbook Aircraft Engine Design Second Edition by Mattingly Heiser and Pratt This program was written to facilitate engineers and students to perform the repetitive calculations and sensitivity studies inherent in aircraft engine conceptual design The program has fourteen 14 constraint types eight 8 contour plots thirteen 13 mission types seven 7 aircraft drag models seven 7 engine thrust models and seven 7 engine fuel consumption TSFC models This program can perform the following analyses a Constraint analysis b Contours of aircraft engine performance c Mission analysis d Engine performance analysis Data windows with input data fields show the user what input data is needed to perform each set of calculations Plotting of results is incorporated into each analysis using the Olectra Chart 6 0 software
15. Aircraft 5 Ve ftisec 2000 Click left mouse button to Vel ins 0 Ps Contour Plot capture xy coordinates Alt kft 0 Pressing the Color Contour Lines button opens the Color Contours window with a plot of the contours generated by the Olectra Chart plotting software This plot format is only able to show the contours ES Color Contours Mel Done Ps Contours AB Off Date _Done File C Program Files 4e D sus AED sus AED cu Standard Day Engine H2 TSFC H2 TR 8 1 1 Aircraft 5 Print TAW 271 3 W75 64 0 paf Beta 0 9 g s 1 0 Thrust 100 Right mouse click for plot Ps ft sec properties EM 200 550 750 800 700 750 EBD 700 EDD 650 550 600 500 550 450 500 4DD 450 350 400 300 350 250 300 200 250 150 200 100 150 50 100 0 50 noc TOGE cape ZO Velocity ft sec The layout of the plot e g the color of the contours and location of the legend can be changed by moving the mouse over the plot and pressing the right mouse button to display the plot properties 3D Chart Control Properties window BH C an Loenbiel Frs les oncle up i i Ax Chartfiroup Tiles Legend General Bader inteso Image About tBalched F nipoubiefiulered UteTroeType per sw C on 13 5 MISSION ANALYSIS When either the Mission Analysis button or the corresponding pull down item in the System Analysis menu is
16. Combat Air Patrol Bes es aN WL b a Acceleration Pt 1 Remove 12 DC amp b Acceleration Pt 2 To d b c Acceleration Pt 3 14 E b d Supersonic Penetration Add 15 L 78H Fire AMRAAMS Mame j1 2 A Warming Lp Change Type Warm up T wing Loading WS Atmosphere Thrust Loading T 4 1 32 Standard Hot Day Weight Fraction at Start Beta 3 Gross Takeoff Weight 4 C ColdDay C Tropical Day Thrust c SL Static T 31600 i AJAS Wing Area S Schedule Pet Empty Weight Scale Engine Done Model User Defined Model Thrust Scale Factor 1 0000 31 The mission summary for a cycle deck engine has two pages The first page shown below for a constant installation loss model is similar to that of the simple engine models Information about the number of engines thrust scale factor and engine controls is now included in the header In addition a column listing the uninstalled thrust F has been added to the right of the previous columns of data Results Im Ei Mission Analysis Version 3 l Date Filename C Program Files AEDeyvs AaF Final Engine AED Models Aircraft 7 Thrust 7 TSFC 7 Standard Day Engine File Name C Program Files AEDsys AaF Final Engine ref Mumber of Engines Thrust Scale Factor Max Compressor Pressure Batic Current Selection Wing Loading WE Thrust Loading T T Weight Fraction Beta Gross Takeoff Weight Thrust i SL
17. Ed p la mdaotc t2 2 14828 Pt Ft4 5 3 2435 Max Temperature at Station 3 go R LPC FR 3 500 mdotc45 21 63 Max 2 Ref RPM LF Spool 0 HFC PR 3 01 Pid 5 Pt5 2 361 Maxx Ref RPM HF Spool 0 mdote amp 2 5 29 54 th Tt4 amp 0 5366 Max Temperature at Station 3600 APM LP spool 96 65 Bypass Ratio 0 754 POPS POP 1 000 RFM HF Spool 36 70 X AS 5 1 1443 AB AB TH 1856 R Enter for na control limit on this property EPR PFtb Ftz 3 18 re Enter D to turn off afterburner Max Thrust 15840 Atmosphere s e Max 1 6356 Engine Station tz f Standard C Hot Day ae an ES Cold Day t Tropical Day Thrust Scale Factor 71 0000 Engine Station ciel I Ip Horus Independent Variable T Perform Calcz Partial Throttle t Mach Number Altitude ft Minimum o rins ust 2o Ambient Temperature TO Fl Maximum 2 Ambient Pressure PO psia step Size fo C Total Temperature Lyg Combustor Tt4 R t Total Temperature Lyg Afterburner Tt A C Exhaust Pressure Ratio POPS No Mach Altitude Day Ho of Lines j Humber of Lines M Color Wide Lines Symbols w Legend 22 After performing a test press the Summary of Test Results button in the Engine Test window to open the Results window and display a comparison of engine performance at the reference and test points as shown below
18. NDOW Selecting the Cycle Deck from the Engine pull down menu on the AEDsys main window opens the Engine Data window shown below and accesses the ONX program press Run ONX button and the input of engine reference data from the ONX program press Input ONX Refr File button Engine Data Engine Cycle Gas Type Number of Engines E Engine Controls Max Temperature at Station 4 Max Compressor Pressure Ratio Max Pressure at Station 3 Max Temperature at Station 3 Max x Ref RPM LP Spool lax Ref RPM HF Spool Installation Loss Model f Constant Loss for Each Leg 0 05 C Loss Model of Chapter 6 Inlet Capture Area 41 Afterbady Area A10 Afterbady Length L Aux Inlet Area Max Mach for Aus Inlet Pressing the Input ONX Refr File button opens a dialog window like that shown below to input an engine reference data file created by the ONX program 2 Files of lupe ONY Reference Data Fies REF Cancel p st madony 19 Selecting the AAF Base Line Engine reference data file in the Open window results in data being read into the Engine Data window and displayed as shown below Note that the initial control limits for the Max Temperature at Station 4 Max Compressor Pressure Ratio and Max Temperature at Station 7 are the design point values No control limits zero values are initially set for the other control limits Engine Data Engine Cycle Turbofan w AB
19. Progress Results Minimum Value Maximum alue Values to be plotted Minin T Maximum O57 Contour Line Increment zu Plot Contour Lines Line Width 1 to 4 2 Color Contour Lines Pressing the Plot Contour Lines button results in the basic contour plot being generated in the Plot window as shown on the next page This plot format will also show the maximum dynamic pressure q maximum lift coefficient Cymax optimum path theta zero lines and Mach lines when selected to be shown The basic plot on the next page shows the maximum dynamic pressure maximum lift coefficient and minimum time to climb path on a P plot Two labels and an arrow have been added to highlight these lines Similar to the basic constraint plot this plot has a mouse activated coordinate capture to facilitate reading the data of the contour plot Ps fs RF EF L D 11 Lift to Drag ratio D T SL Drag to Thrust at SLS D Ts Alpha Thrust lapse Pg 23 38 CimbAde Pg 33 Weight specific excess power P _ Pg 22 48 Fuel consumed specific work f Pg 59 92 Minimum fuel to climb Textbook Ref Optimum Path RF Range factor RF Pg 65 Maximum L D Plot Ee File CAProgram Files WEDsys EDsys AED D ate Ps rum 0 max 850 mer 50 ft sec Standard Day Atmosphere 7l F A Eu WS d Th z 1 3 Beta 0 3 g s 1 00 CLm 2 0 Qmx 22133 Tmxz1 TR 2141 AB off Engine 2
20. Properties window A Lan Laonbiel Prep hie ees EX 10 4 CONTOUR PLOTS When either the Contour Plots button or the corresponding pull down item in the System Analysis menu is selected the Contour Plot Data Window 1s displayed like that shown below This program feature allows the user to generate eight 8 different contour plots and display them in two 2 different plot formats Calculations are performed at the wing loading W70 5 thrust loading Ts W 70 weight fraction p and number of g s n load factor over the range of altitudes and velocities using the selected altitude model After the contour plot data has been calculated the Plot Contour Lines and Color Contour Lines buttons are enabled The user can enter the desired minima maxima and plot increments Contour Plot Data Wing Loading W S E4 psf Thrust Loading T 4 aa Weight Fraction Beta 0 9 Number of g s n 1i M asimim Lift Coeff E L max M asimur Dynamic Pressure O mas 2133 psf Percent of Maximum Thrust 1 MN C DR Mo limit plotted for zero input Pm Range ot Range of Velocities Altitudes Optimum Path med Tk ft lv Yes T No Minimum 100 jo Theta 0 Lines blasman 2000 0 Ir Yes M No Mach Line s Increment 50 2 Yes v No Contour Jw Ps fs RF BN L D D Tc85L Alpha Climb Angle Atmosphere Standard Cold Day Hot Gay Tropic Day
21. Provides links to the associated AEDsys software programs Units Pull down Menu The user can select British English BE or SI unit systems When unit system changes the data are converted to the new unit system 3 CONSTRAINT ANALYSIS When either the Constraint Analysis button or the corresponding pull down item in the System Analysis menu is selected a Constraint Window is displayed like that shown below Constraint Rose D el amp Mame Horizontal Acceleration akea E RE M E 30 2 4 Supersonic Penetration Escape Dash Type D Horizontal Acceleration 3 C Combat Turn 1 Bet Don 4 L Combat Turn 2 ef 5 D Horizontal Acceleration dede Bb H Landing Temperature H Constraint YA Maximum Mach Number Velocity fts Mach number dvd It s 2 LDA Fraction of masimum thrust Engine amp B 1 0N0 0FF E Hemove Add Change Hame Horizontal Acceleration Type D Horizontal Acceleration Calculate Wing Loading Thrust een W S psf Loading T w Standard Lem 7g a C Cold Day Masi EMEN eu e Hot Day Plot Plot Sit 5 0 1 Tropical Day The constraints of interest can be constructed using the upper portion of this window Double clicking on an item in the upper left window causes the data for that constraint to be displayed on the right side of the window for editing The constraint analysis can model each of the fourteen 14 constraints of the textbook The type of constraint
22. am Files AEDsys A4F Final Engine ref Mumber of Engines e Thrust Scale Factor 1 0000 Max Compressor Pressure Patio 2o 00 Area 1 3 52 Area LO 5 15 M Lnoth 4 61 Lrealux 3 52 MO Aux 0 300 Current Selection Wing Loading W 51 64 00 pet Thrust Loading T T L200 Weight Fraction Beta 1 0000 Gross Takeoff Weight 4000 1b Thrust 4 SLS 31650 1b Wing Area 8 375 00 sf Leg Mame Mach Altitude AO A0 Aread Thrust TSFC Phi I tH Limit Trad Tt ft ft z fre ilb l hri l l z n 0 0nnn 0 000 2 351 1 793 16727 0 765818 0 05596 Ttd Max 3200 0 e l z B 0n0n 0 000 2 942 2 929 265802 1 761415 0 01342 Tt4 Max 3200 0 3600 0 sgh ee LLTEEL 000 2 622 2 937 26612 1 784675 0 00227 Trt Max 3200 0 3600 0 42 3 D 0 4410 000 2 691 1 829 14957 0 882868 0 00257 Ttd Max 3200 0 5 2 3 Ea 0 7750 3000 2 683 2 131 15793 0 528406 0 01050 FIC Max alaz 6 3 Eb 0 8750 23000 O Lee 2579 n 90906z 0 02944 PIC Max 2910 0 7 3 Ec O lt 3000 36000 2e o74 2 264 5451 0 855976 0 03253 PIC Max 2652 95 5 3 4 O 3000 41632 2 343 1 566 2475 0 936350 0 11608 PIC Max e370 0 3 4 6 Drop Weight LU 5 6 0 69956 30000 1 962 1 681 2265 0 915476 0 123859 Thrust DPrag 2064 6 ll amp 7a 0 9178 30000 2 876 3 878 l4242 1 657901 0 01095 PIC Max 2716 8 3600 0 lz 6 7h 1 0300 30000 2 5989 4 359 158178 1 869026 0 04080 FIC Max 947 7 3600 0 l3 amp 7c 1 3650 30000 3 018 4 990 24479 1 789288 0 01436 Ttd Max 3200 0 3600 0 l4 6 7d 1 6000 30000 2 882 3 083 10748 1 079813 0 0
23. amp S Wing Area amp Empty Weight WE WIOU 2 270 WTIO0 0 130 e 1 0000 23 00 64 00 1 3200 1 0000 24000 31660 275 00 14683 User Defined Model Mame PI Beta Beta Ut Chg Drag Thrust Time Dist Thrust iF initial final Ib Ib ilh sec Tim ilb 1 l 0 993110 1 00000 0 93110 214 16555 60 0 Oo 00 17713 E l B 0 99534 0 99110 0 98645 111 375 eb58n08 darc 0 13 ele 3 l C 0 99833 0 98643 0 985484 40 375 25339 3 0 O 10 26672 47 3 D 0 99423 0 98484 0 97915 136 e407 14246 37 3 3 14 14956 The second summary page lists the required 4 or 45 and Ag areas TSFC installation loss control limit maximum engine temperatures etc This area data is very useful for sizing the inlet 4 and the afterbody 410 Z Results Mil x Mission Analysis Version 3 l Filename Models Aircraft 7 Thrust 7 Egine File Name Date EI Cri Program Files AEDsye AaF Final Engine AED TSFC 7 Standard Day Ci Program FilesyAEDZzysA A F Final Engine ref Number of Engines e Thrust Scale Factor l nnau Max Compressor Pressure Ratio 26 00 Current Selection Wing Loading Wy 64 00 pet Thrust Loading T T 1 3200 Weight Fraction Beta 1 00 Gross Takeoff Weight 24000 1b Thrust m SLS 31660 lb Wing Area amp 375 00 f Mame Mach Altitude AO 40 Areas Thrust TSEC Phi ITN Limit Ttd Tt ft fr 2 ft z ilb l hr l A 0 000d 2000 851 1 783 16833 0 760994 0 05000 Tt4 Max 3200 0 e B
24. en calculated the partial throttle plot buttons become visible in the lower right of the engine test window as shown below Independent Variable Mach Number Perform Calcs C Altitude ft Minimum T Min Thrust Ho C Ambient Temperature TO R Maximum 2 Plots C Ambient Pressure PO psia step Size n Throttle Hook s Total Temperature Lyg Combustor Tt4 A hlo of Lines T Boating Liniefs Total Temperature Lvg Afterburner Tt Fi Fan HPE C Exhaust Pressure Ratio P P3 LPT No Mach Altitude Day Number of Lines 1 fero Plot File MW Color wide Lines Symbols M Legend 28 As an example the partial throttle performance was calculated at the following altitude Mach number conditions in a standard altitude 0 kft 0 0M 30 kft 0 9M and 30 kft 1 5M The uninstalled throttle hooks thrust specific fuel consumption versus thrust are displayed below and the fan operating line is shown on the next page 23 Partial Throttle Plot Done Print Throttle Hook Date Engine File CAProagram Files AbDsys 4APF Final Engine ret LE Right mouse click for plot properties Legend Mach Alt D ay D DE O0K Ft Std 3h S0k fe Std TOM SUK Std Thrust Specific Fuel Consumption bm hn bf 0 e000 4000 e000 6000 10000 12000 14000 16000 Thrust If 29 I 23 Partial Throttle Plot Engine File CAPra
25. g SRE D 33566 ARE ll9z2 4520 17514 mo M 7 ebb5bz35 4 Independent Variable f Mach Number C Altitude ft Ambient Temperature TO Fl C Ambient Pressure PO psia Total Temperature Lyg Combustor TH4 Fi Partial Throttle Mininnum T Min Thrust 20 Maximum 17 6 Step size 006 Ma of Li Total Temperature Lvg Afterburner Tt R LE C Exhaust Pressure Ratio PO FS Plot No Mach Altitude Day R Plot Li 1 0 00M 00 0kft Standard Remove Pit Eine upberoflines 0 ero Plot File W Color Wide Lines Symbols w Legend The engine performance can be calculated at full throttle military and maximum power and plotted using the lower left of the Engine Test window as shown above After the Perform Calcs button is pressed the Results window is opened and the predicted engine performance displayed as shown below The program saves the variation of the engine performance with the independent variable for later plotting The status of the saved plot data is updated in the Engine Test window Up to 21 plot lines can be plotted Results LEDevs Version 3 Date Engine File C Program Files AEDsys AaF Final Engine ref Performance Calcs Mach 0 00 Altitude O fct TO 518 67 BR Standard Day eee Mixed Flow Turbofan Engine Mo Thrust 5 udot pic pif Alpha PES ES Pith Ttd AO AO Areas Limit 0 01 15640 1 6956 142 36 28 02 3 500 00 754 2 9
26. gram Files AEDsys AAF Final Engine ret Fan Pressure Ratio Fan Operating Line Date Right mouse click For plot properties Legend Mach Alt D ay 0 0M DUKE Std OSM 3UkIE Std 1 5 430K ft Std fal all 90 100 110 120 130 140 150 Corrected Mass Flow Rate lbmsec 30 9 ENGINE CYCLE DECK MODEL MISSION ANALYSIS Once a reference engine data has been input into the AEDsys program and the installation loss model selected in the Engine Test window mission analysis can be performed of the reference engine installed in the aircraft Pressing the Mission button on the AEDsys main window opens the Mission window shown below Note that the mission leg data now has maximum 77 and Ta when applicable for each mission leg This data needs to be set to the appropriate maximum s for each mission leg For engines with convergent divergent exhaust nozzles an exit area 49 43 schedule can be input versus Mach number during the exhaust nozzle design It is not recommended to select the 45 45 schedule until that phase of the design MESE Ae eres phe Mame 1 24 Warring Up 1 1 24 Warming Up T E IMax S0 2 D 1 28 Takeoff Acceleration PPE P b 4 J 1 20 Takeott Rotation Altitude ft 4 B 230 Acceleration T p 5 C 23Ea Clmb Accel Pt1 emperature Fi 5 C 23Eb Climb Accel Pt 2 Time sec E 23Ec Climb ccel Pt 3 Engine 46 1 0n0 0ff B G 3 4 Subsonic Cruise Maximum Tt R d L 4 5 Descend 10 H 55
27. h each constraint line numbered in accordance with its number in the Constraint window This plot has a mouse activated coordinate capture to facilitate reading the boundaries of the solution space An example plot is shown on the next page with the coordinates of the location of the mouse cross hairs location captured and displayed below the plot Plot aS File CAProgram Files AED AF Chapters 2and3 4ED Date TR 2107 Aircraft 5 TAT 0 WAYS pst 200 se EIU HET NE Click left mouse button to W5 psf 56 40 pam Constraint Diagram capture cco discs Tf 2 1133 Prnt Pressing the Plot button opens the Color Constraint window with a plot of the constraint lines generated by the Olectra Chart plotting software The user can select to show the plot legend as done below or generate a larger plot ETE Constraints Constraint Diagram Date File C Program Filess amp ED sus l Chapters 2 and 3 5ED Engine H2 TH 1 07 Aircraft 5 Right mouse click for plot properties Constraint 1 Takeoff 2 Supersonic Penetration amp Escape Dash 3 Combat Turn 1 4 Combat Turn 2 5 Horizontal Acceleration b Landing Maximum Mach Number Thrust Loading TAW 5n 100 150 2 nt Wing Loading S ost The layout of the plot e g the color of the lines and location of the legend can be changed by moving the mouse over the plot and pressing the right mouse button to display the plot properties 2D Chart Control
28. ion such that the payload is removed at the end of the mission the final weight of the aircraft can be compared to the predicted empty weight Results FE x Leg Oo M n wd Mi Mission Analysis Version 3 l Late Filename C Program Files 4EDesvrs AEDesss AED Models Aircraft 5 Thrust TSFC Standard Lay Throttle Patio 1 1 Current Selection Wing Loading W S3 64 00 pet Thrust Loading T T 1 3000 Weight Fraction Beta 1 000d Gross Takeoff Weight 47000 lb Thrust M SLS 545600 lb Wing Area 8 656 25 ef Empty Weight El Ib User Defined Model WE WIU 2 106 WlO O 130 Name PI Beta Beta Wr Chg Drag Thrust Time Dist initial final i Ib Ib i lb Sec Yuta l 0 987854 1 00000 0 98764 511 32760 60 0 o 00 l B O 39614 0 985784 0 98403 160 12882 64910 5 6 0 03 l z C 0 99807 0 95403 0 98215 au 126882 ew d 3 0 O 10 2 3 D 0 99004 0 98213 0 97235 411 4764 5581859 14 3 1 20 2 3 Ea 0 98815 O 97235 0 96083 454 6755 60330 16 5 2 29 2 3 Eb 0 99135 0 96083 0 95255 346 5645 36417 20 85 3 02 2 3 Ec O 39401 0 95255 0 346855 233 4523 21730 d 3 56 3 4 O 94071 0 94655 O 89071 355 4766 4765 7070 6 ESS 715 4 5 0 99075 0 89071 0 88247 346 10700 19553 67 7 11 53 5 6 0 93595 0 88247 0 82595 374 elzee elzee CIC 55 47 Delive 1 00000 0 82595 077017 e343 6 7a 0 958698 077017 0 735704 135 30307 309307 126 9 0g 6 b 0 96235 0 73704 0 70929 1165 ezl5b5 22155 142 8 Oo 00 7 3 0 98504 0
29. ithin the Engine Test window eee un eee Ss E Component Interfaces Mach fi 1 log Mach 2 0 5 Mach 32 nos Mach 5 0 6 Mach 7 0 5 Desi Interface Quantities Version 3 l Late a Filename C Program Files AEDs ys AEDs zs LED Engine File Name C Program Files amp AEDZzys F Base Line Engine ref Thrust Scale Factor 1 0000 Station m dot gamma Pt Tt P T Mach Velocity Area Area I i lbm z ipsia Bi ipsia EI ft s tie ey I frt z ilbf 200 00 1 4000 11 311 554 33 3 306 390 50 1 4510 1405 54 6 227 5 440 l11702 8 l 200 00 1 4000 11 021 554 93 7 30 491 96 0 8000 869 850 Bote 5 583 ll44z 8 00 00 1 4000 10 581 554 93 8 3920 528 51 0 5000 563 46 T vI 5 816 l3511 7 l3 200 00 1 4000 41 2764 858 99 36 991 832 57 0 3984 563 46 360 1 655 19270 4 core 136 06 1 4000 41 264 858 99 36 991 832 57 0 3984 563 46 2 043 1 281 13302 0 bypass 61 94 1 4000 41 764 856 99 36 991 832 567 0 3984 563 46 0 917 0 575 5968 3 2 5 136 06 1 4000 41 264 858 99 36 991 832 57 0 3984 563 46 2 043 1 281 13302 0 3 0 136 06 1 4000 211 612 1443 36 196 363 1416 94 0 3054 563 46 0 648 0 324 z S94l 1 3 1 122 97 1 4000 211 612 1443 36 196 363 1416 94 0 3054 563 46 0 577 0 288 l8637 6 t e 122 87 1 4000 209 496 1443 36 z 08 560 1441 52 0 0800 1486 89 113 0 291 64037_1 MB fuel 3 7710 4 126 64 1 3000 401 032 3400 00 108 708 2782 61 1 0000 2453 05 0 476 0 476 l 7291 358 4 1 l33 54 1 3000 3095 23 4 4 133 54 1 3000 685 060 2594 07 4 5 140 45 1 3000 8
30. mber and engine throttle 7 4 perform constraint analysis and generate contour plots When an AED data file is saved with a reference engine the reference data for that engine is saved inside the AED data file Basic Steps 1 Design an engine in ONX program at a single design point and save the Reference Engine Data file REF 2 Using the AEDsys program select Cycle Deck under Engine pull down menu or press the Engine Data button of AEDsys program and read in the ONX Reference Engine Data file REF 3 Input engine control values Run Constraint analysis to determine the required thrust loading Ts Wro for the selected wing loading Wro S Run Mission analysis and determine fuel used If engine is too small for any flight condition increase the system Ts W as required and rerun the mission The engine is automatically scaled TSF in accordance with T Wro at the start of the mission analysis 4 Repeat steps 1 through 3 for another engine design until desired results are reached 5 Review second summary sheet of mission analysis and find largest required A and Ajo 6 Select Chapter 6 Installation Model in Engine Data screen Input design 41 Ajo and nozzle length L Determine mission performance with this installation loss model Programs Data Files Name ONX On Design Data File 4 ONX Reference Data File V4 7 REE AEDsys AEDsys Data File lt AED 18 7 ENGINE CYCLE DECK MODEL ENGINE DATA WI
31. nu 0 0 0 2000 2 842 2 929 25808 1 829250 0 05000 Tt4 Max s200 0 3600 0 p Ge 0 l1l8 1l 2000 2 822 2 937 25339 1 874342 0 05000 Tt4 Max S200 0 3600 0 4 D 0 4410 2000 2 691 1 829 3 ld4z4 amp 0 326946 0 05000 Tt4 Max 3200 0 5 Ea 0 7750 S000 803 2 131 115163 0 967004 0 05000 PIC Max alaz amp Eb 0 8750 z3 0 0 Egg cy 35 S376 0 928741 0 05000 PIC Max 2310 0 32 The mission performance of a cycle deck engine with the inlet and afterbody sized using the methods of Chapter 6 can be determined similar to the above analysis for constant installation loss Based on the previous type of mission analysis the Chapter 6 model inlet and afterbody data is first entered into the appropriate data fields on the Engine Test window see below before the mission analysis 1s performed Installation Loss Model Constant Loss for Each Leg f Loss Model of Chapter 6 Inlet Capture Area Al Afterbady Area A10 Afterbady Length L Aux Inlet amp rea Mas Mach for 4ux Inlet The first page of the results and the top of the two summary pages now display the inlet and afterbody information as shown below for the first results page The Results window for each mission leg now gives the data used to calculate the installation losses and the results Results Im X Models Aircraft 7 Thrust 7 TSFC 7 Standard Day Engine File Name C Program Files AEDsys A4F Final Engine ref Mumber of Engines e Thrust Scale Factor 1 0000 Ma
32. r performing a test press the Engine Station Test Results button in the Engine Test window to open the Engine Station window and display the component interface flow properties as shown below These are based on the annular flow areas calculated using the Component Interface button within the Engine Data window If the Component Interface button has not been pressed and the annular flow areas calculated then only the mass flow rates ratio of specific heats and total properties are shown for each engine station mi Engine Stations Test Results at Engine Stations rAEDzys Ver 3 l Filename Engine File Mame Thrust Scale Factor Altitude 0 ft Station m dot lbnr s ldz 36 1 l 142 36 1 e 142 36 1 l3 142 36 1 core 51 16 1 bypass 6l z0 1 2 4 51 16 1 S 51 16 1 dul FE d 1 S asks 2 24 1 MB fuel 1 8423 4 74 05 1 4 1 78 14 1 4 4 78 14 1 4 5 az 19 1 5 82 19 1 6 52 19 I l 6l z0 1 SE Laan 39 1 AB fuel 5 86181 7 143 01 1 Print am a 4000 4000 4000 4000 4000 4000 4000 4000 4000 4000 3000 3000 3000 3000 3000 3000 4000 3360 3000 Ft lpsiai 14 14 14 43 43 43 43 395 395 2391 375 115 43 43 43 47 4d 6397 697 103 373 3279 3279 373 z285 ES 335 Les 779 03l sl 3 240 275 Tt Percent Thrust BR 513 518 513 wb TTS TREE TTS 1500 1500 1500 z983 z891 ezY4l eI 1556 1556
33. s must be entered in increasing value Drag Eqn Engine Pull down Menu The user can choose from the basic Thrust and TSFC models of Chapters 2 and 3 respectively or the Cycle Deck that uses the performance engine models of Chapter 5 When Cycle Deck model is selected the Engine Data Window is opened for input of an engine reference data file generated by the ONX program When Thrust is highlighted the user can select from seven 7 basic thrust models The first four 4 models correspond to the models in Section 2 3 2 When one of these four thrust models is selected the Throttle Ratio TR window opens for user input E ngine TH When the User Input Engine Model is selected model 5 the window opens for data input as shown below When the User Input Values model is selected model 6 a data field 1s created in the respective constraint analysis for user input of the thrust lapse a for that constraint When Cycle Deck model is selected the Engine Data Window is opened for input of an engine reference data file generated by the ONX program Eg User Input Engine Thrust Model fo Jo d 2 fo CES User can select from six 6 basic TSFC models The first four 4 models correspond to the models in Section 3 3 2 of Aircraft Engine Design Second Edition When the User Input Engine Model is selected model 5 the following window opens for data input 3 User Input Engine TSFC Model fo fe fo Links Pull down Menu
34. ssion legs and their data the mission can be flown one leg at a time starting with the aircraft system design point thrust loading and wing loading initial weight fraction 6 and gross takeoff weight GTOW Pressing the Calculate button at the bottom of the Mission window opens the Results window and displays the initial design data and results for the first mission leg as shown below ES Results WORST Mts ET Mission Analysis Version 3 l Date Filename C Program Files AEDeyvs AEDsys AED Models Aircraft 5 Thrust 2 TSFC 2 Standard Day Throttle Patio LL Current Selection Wing Loading Us pet Thrust Loading T T Weight Fraction Beta Gross Takeoff Weight Thrust B SLS Wing Area amp Empty Weight User Defined WE WTO 2 106 WT O0 i 0 130 Mission Leg 1 Name l zZ Warming Up Type I Warm up Altitude ift Temperature iR Time sec Engine AB 1l 0n 0 0ff RESULTS O80Et 00 Thet al s ET 000E 00 Delta 1 000E 00 O00E oO1 Cl C2 M 9 0 00E 01 lbm i hr lbf _o7SE O1 TSFC 9 352E 01 lbm ihr lbf nET U D Beta zZ 3_676E 01 15 The Summary and Plot buttons on the Mission window become active after at least one mission leg 1s calculated After calculation of basic engine thrust model and fuel consumption model of Chapters 2 and 3 model 1 5 pressing the Summary button displays a single page summary of the mission results as shown below If the user constructs the miss
35. straint has been calculated the Plot and Plot buttons are enabled Results TE X Constraint Analysis Version 3 i Late ni FILE C 4 Program Files AEDsysiAaF Chapters and 3 AED Page lof 7 CONSTRAINT 1 TYPE F TAREOFF NO OBSTACLE Beta weight fraction L Altitude ift 2000 Temperature ii Sed Mach number during TO roll LL CLE 0654 CL max ETO l TO friction coeff 05 Rotation time tE si 3 Total TO distance sTO ift 1500 Engine AB 1 ON O 0FF 1 Next Constraint ENGINE MODEL AIRCRAFT MODEL 5 ALPHA oO 3006 TE 1 07 TSL WTO WTS SC SE VEL pet ft ft fps 32 443E 01 1 000E O2 1 49E 03 7 96Et00 2 65E 00 3 4dSE 01 5 0D00ETD0D l 32ET03 1 78E 0 5 93ET Ul 3 599E O1l 1 000E 01 1 25EtO3 52Et02 39E 01 3 957E l l 5 00ET Ul 1 19E 03 3 08E 0 1 03E 02 d 439E Ul 000E 01 1 14E 03 3 556Ef0Z 1 19E 02 5 00E 0l SOGE OL 1 10E 03 3 98bEf 0Z 1 33E 02 622E O1l 3 000ETDl 1_ O6E tO3 4_36Et02 1 45E 02 6 z94E l 3 500ET0l1 1 03E 03 4_71EtO2 1 57E 02 lzE l 4 Q000E O1l 9 9 7EF Z 5 03ET0Z2 1 68E 02 7 7 4E O1l 4_500E O1l 9 66E 0E S_ 34Et02 1 78E 02 8 S581E Ol 5 000E 01 9_ S7EtO 2 5 63E 0 1 58E 02 9 431E 0O1 5 5D 0ETDl 9_10EtO2 5 _SOE OZ 1 97E 02 1 032ZE OO0 6 OO0E OL 8 84E 0z 6_ 16EtO02 2 05E 02 1 126E 0O0 amp 6 500ET0l1 S_ 59E 02 6 41Et02 14E 02 Pressing the Plot button displays the Plot window containing a basic plot of the constraints calculated wit
36. the box displays a list of mission leg types for user selection as shown below if needed the user can scroll to the desired leg Constant Speed Climb 4 Constant Speed Climb a Warm up Horizontal Acceleration J Takeoff Rotation Climb and Acceleration K Constant Energy Height Maneuver Takeoff Acceleration L Deliver Payload Constant Altitude Speed Cruise M Climb Descend Angle Constant Altitude S peed Turm Best Cruise Mach and Altitude Lotter After a new mission leg type is selected the user presses the Change button to change the current mission leg and the appropriate data list is shown on the right Press the Add button to add a new leg at the current leg number Press the Remove button to remove the current leg The Atmosphere radio buttons allow the user to specify the atmospheric model that is to be used for auto update of the air temperature for new altitude data For flight conditions corresponding to one of these atmospheric models enter the altitude first and then enter the desired temperature 14 Pressing the Model button under Empty Weight displays the Empty Weight Model window that allows the user to select one of the models of Section 3 3 1 or enter their own model This feature is useful when trying to fly mission and close on a empty weight that will meet the requirements of the RFP i 7 oc el E Ir os 005 After the mission has been constructed by entering the mi
37. the user is asked if they would like this new value to be used in all mission legs After an engine reference data file has been loaded into the AEDsys program this engine s reference data 1s used in the engine performance model for all analyses and the Engine Data button and Engine Test button are added to the AEDsys Main window as shown below to facilitate navigation 20 File System Analysis Aircraft Drag Engine Links Units Status File C Documents and Settings Jack Mu Cocurments s oftware wae Dens 3 0001 AE Deps AED Drag 5 Future Fighter Units BE Engine File C Program Files 4EDsye 44F Base Line Engine rel Inlet Compressor Turbine Nozzle Atmosphere EGIL Combustion Man Burner Afterburner Calculator The Engine Data window is also the window for entering the Number of Engines Engine Control limits and the Installation Loss Model In addition pressing the Scale Thrust button will scale the engine thrust calculate the Thrust Scale Factor so that the specified number of engines produce the thrust specified on the Mission Analysis window Pressing the Component Interface button opens the Component Interfaces window Press the Calculate button to display the component flow properties based on the user input Mach number data initial estimates at the top of the window and the Thrust Scale Factor as shown below The resulting annular flow areas are used in Engine Station Test Results calculations w
38. x Compressor Pressure Patio 2o 00 Area l 3 519 Area 10 5 153 HM Lngth Area Aux 3 519 MO Aux 0 300 Current Selection Wing Loading W 51 64 00 pet Thrust Loading T T 1 3200 Weight Fraction Beta 1 0000 Gross Takeoff Weight 24000 Thrust SLS 31680 Wing Area 5 3275 00 Empty Weight 146853 User Defined Model WE WIO 2 270 WTO O 130 Mission Leg 1 Name l A Warming Up Type I Warm up Altitude ift Z O00 Temperature Bij Time sec Engine AB 1 0n 0 0ff Maximum Ttd E RESULTS 673EtO4 lb TSFC 7 658E 01 lbm ihr lbf 00EtOS E Limit It4 Max S51EtOO ft z Area S8 1 793E 00 ft z S4SE O Al A0 34E 00 O87E O2 410 40 ae oe oe 661E O1 CD Noz S53E U4 588E z Phi N 1 229E 08 311E l1 TSFC 7 658E 01 lbm i hr lbf 000E 00 Beta 311E 01 Foc mo0ad 23 20 IMS Hoz Phi I PI Beta 1 Print Mext Leg P inb nbenrmrmtunv 33 The first and second mission summary pages for the installation loss model of Chapter 6 is very similar to those of the constant installation loss model with the exception of the additional information in the header The second mission summary page is presented below for the AAF showing the variation in installation losses with flight condition Results Im X Mission Analysis Version 3 l Date F Filename C FProgram Files AEDesvwes AAF Final Engine AED Models Aircraft 7 Thrust 7 TSFC 7 Standard Day Egine File Mame C Progr
39. z amp 6z23 3 406 Tt4 Max 0 950 18933 1 9365 1838 83 23 09 3 025 O 820 4 2704 0 4349 3700 0 2 565 3 445 Tt4 Max 0 95 19230 1 9487 205 99 zz zZ 2 9541 0 534 4 3751 0 4375 3200 0 2 508 3 487 Tt4 Max 1 00 19562 1 9601 209 15 21 36 2 857 0 549 4 4882 0 4401 3200 0 2 450 3 531 Tt Max 1 05 139695 1 59717 Zzl4 64 fFO_ 51 2 775 0 8565 4 6042 0 44350 3700 0 2 395 3 577 Tt4 Max 1 10 20244 1 9831 220 40 19 67 694 O 1862 4 7259 0 4459 3200 0 2 347 3 625 Tt4 Max 1 15 20620 1 9940 zz56 51 18 85 2 614 0 900 4 8551 0 4490 3200 0 2 307 3 676 Tt4 Max 1 20 21025 2 0043 233 01 18 06 2 537 0 915 4 93527 O 4522 3200 0 2 275 3 7239 Tt4 Max 25 As an example of a performance plot the performance of the AAF Final Engine is calculated at maximum power over the range of Mach numbers listed for each altitude listed below for a standard day atmosphere Altitude kft ee PE Once these calculations were done the uninstalled thrust was plotted and is shown below The uninstalled thrust specific fuel consumption S is shown on the next page Engine Performance Plot Done Thrust AB On Date Engine File C Program FillesysEDeysyAAF Final Engine ret Hight mouse click for plot properties Legend Alt D ay m OOk Std 5 IDE Std 20k Std B akft Std a 3b it Std 40k rte Std 00 Oe 04 06 08 TW 123 14 16 18 20 Mach at Station 0 26 ZEE ngine Performance Plot s
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