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PROPID User Manual - UIUC Applied Aerodynamics Group

1. At anytime following the CH_TW line the blade chord and twist distributions can be written by using 94 and 95 for the chord and 99 and 100 for the twist The blade Reynolds number is calculated using the kinematic viscosity of air at standard sea level conditions v 1 5723 x 10 ft sec The air velocity used to calculate the Reynolds number contains the components from the freestream rotational and induced velocities 7 2 2 File Format Each data case is written to its own individual ASCII file with the name ftn dat where xxx is the IPRT number listed earlier Results are presented in column format in each file The first column is the blade span station usually nondimensionalized by blade radius blade span station for files for 76 95 96 97 and 99 are in feet The number of span stations is the same as NS defined in the input file see Chap B For the geometry output files 94 95 96 97 99 and 100 the output has been extrapolated to include the geometry at the blade tip The second column in each output file begins the results of the 1D sweep Results from each case in the 1D sweep is presented in a separate column in the output file The exceptions are the output for the geometry 94 95 96 97 99 and 100 and the Reynolds number 76 The output for the Reynolds number is only given for the last case in the 1D sweep Example PITCH_DP 1 RPM_DP 1 WIND_SWEEP 5 30 3 2 21 1D SWEEP WRITE FILES 85 95 The lines ab
2. gt gt 1 iteration 3 calculating sensitivities for newtl design parameter 1 32 residues for newtl equations fnt1 1 1 0 00362 valuei 95 00362 deltasi 0 07284 clamp1 1 500 select option 0 stop iteration for current stage number of consecutive iterations 999 to stop execution 99 more options gt gt 0 In this case from the Select option prompt 2 is entered so that 2 consecutive iterations are performed The gt gt notation is used to denote this user input For the first iteration the clamp is reached and the magnitude of the step is reduced to the clamp size After the first two iterations one more iteration is then performed to reduce the residue further At anytime 999 could have been entered to stop the program 99 is used to enter another options menu to interactively double or halve the clamp sizes in case convergence is slow gt increase the clamp sizes or in case the solution begins to diverge gt decrease the clamp sizes Once a blade has converged the converged input data can be written out to file ftn021 dat with the DUMP_PROPID line given by DUMP_PROPID The contents of this new output file can then be substituted back into the original input file as the design process continues As an alternative a PROP93 PROPSH data file can be written out to file ftn022 dat by using DUMP_PROP93 JDP where JDP is the design point Additional NEWT1 lines are listed as follo
3. value2 65 O0Ooo0o0o0o0000OrrrerrrooO 9 140 79974 264 00012 999 97396 1 00002 0 33301 95002 90003 29996 24998 19999 14999 10002 05002 33301 33301 33298 33299 33299 33299 33301 33301 7 with step limit 0 333 at design point rpm 1 pitch 1 xj 7 with step limit 0 75 0 02 0 02 select option 0 stop iteration for current stage number of consecutive iterations 999 to stop execution 99 more options gt gt 3 in consecutive iteration mode iteration 1 calculating sensitivities calculating sensitivities calculating calculating calculating calculating calculating calculating calculating calculating calculating calculating calculating calculating calculating calculating calculating calculating calculating calculating calculating newti newti for for newt1 newt1 newt1 newt2 newt2 for for for for for sensitivities sensitivities sensitivities sensitivities sensitivities newt2 newt2 newt2 newt2 newt2 for for for for for sensitivities sensitivities sensitivities sensitivities sensitivities newt2 newt2 newt2 newt2 newt2 newt2 for for for for for for sensitivities sensitivities sensitivities sensitivities sensitivities sensitivities newt2 newt2 newt2 for for for sensitivities sensitivities sensitivities residues for newt1 fnti_1 1 fnt1 1 2 fnt1_1 3 fnt1 1 4 0 eg
4. 0 00000 value2 1 15000 deltas2 0 00000 clamp2 0 750 fnt2_1 7 0 00000 value2 1 10000 deltas2 0 00001 clamp2 0 750 fnt2_1 8 0 00000 value2 1 05000 deltas2 0 00001 clamp2 0 750 fnt2_1 9 0 00000 value2 0 33300 deltas2 0 00000 clamp2 0 020 fnt2_1 10 0 00000 value2 0 33300 deltas2 0 00000 clamp2 0 020 fnt2_1 11 0 00001 value2 0 33301 deltas2 0 00000 clamp2 0 020 fnt2_1 12 0 00000 value2 0 33300 deltas2 0 00000 clamp2 0 020 fnt2_1 13 0 00000 value2 0 33300 deltas2 0 00000 68 clamp2 0 020 69 0 00000 0 00000 0 00000 0 00001 0 00003 0 00000 0 00001 0 00000 0 00000 fnt2 1 14 0 00000 value2 0 33300 deltas2 clamp2 0 020 fnt2 1 15 0 00000 value2 0 33300 deltas2 clamp2 0 020 fnt2 1 16 0 00000 value2 0 33300 deltas2 clamp2 0 020 iteration 3 calculating sensitivities for newtl design parameter 1 calculating sensitivities for newtl design parameter 2 calculating sensitivities for newti design parameter 3 calculating sensitivities for newtl design parameter 4 calculating sensitivities for newt1 design parameter 5 calculating sensitivities for newt2 design parameter 1 calculating sensitivities for newt2 design parameter 2 calculating sensitivities for newt2 design parameter 3 calculating sensitivities for newt2 design parameter 4 calculating sensitivities fo
5. converged solution for stage 1 As the output indicates when a NEWT1 or NEWT2 line is given the specifications are echoed to the screen for verification The IDES line initiates the iteration which in this case will be performed automatically since TOL1 is specified Stage 1 indicates that this is the first time an iteration sequence has been initiated If a second IDES line were to follow later then that iteration sequence would be referred to as Stage 2 and so on After the IDES line PROPID determines the peak power maximum power over the specified wind speed range and determines the difference between the actual peak power and the specified peak power the residue which in this case is approximately 16 kW In other words the actual peak power is nearly 80 kW rather than the specified 95 kW Since the difference is not less than 0 1 kW iteration occurs In the Newton iteration method the sensitivity of the peak power to the pitch is determined and the step size is set at 1 5 deg Thus in this example the clamp is enforced for the first step in the iteration The iteration is performed again until convergence is achieved Example DP 1 64 2 00 15 000 2 NEWT1ISWP 300 95 25 50 1 11 999 131 1 5 IDES This example which is similar to the last illustrates the interactive iteration mode The TOL1 parameter is left unspecified but the 1 5 deg clamp is still used The interactive iteration mode is most useful when starting
6. effects the lift coefficient of the airfoils can be incremented bumped up or down using the line BUMPCL CLBUMP JAF where CLBUMP cl increment to add JAF index of airfoil to bump default is to apply increment to all airfoils To increment the drag use BUMPCD CDBUMP JAF JBPMODE CDALFA1 CDALFA2 where CDBUMP cd increment or scale factor JAF index of airfoil to bump default applies increment to all airfoils JBPMODE 1 gt bump becomes a scale factor eg 1 5 gives 50 more drag 2 gt blend in the scale factor CDALFA1 scale factor is CDBUMP CDSCALE and goes linearly to a value of 1 CDALFA2 CDALFA1 2 used with JBPMODE is 2 43 In similar fashion the angle of attack of the airfoil data can be incremented using this line BUMPALPHA ALPHABUMP where ALPHABUMP add the increment but does not change the last point 27 5 deg In each case if one or more of these lines are used they must come before any analysis and thereafter the increment or decrement remains CDFAC Line Scale the drag by a factor with CDFAC CDFAC where CDFAC scale factor to apply to all Cd during analysis CHORD BASE Line This is an optional way to enter the chord and twist distributions Enter the base chord then relative chord and twist distributions At least two points are reguired for the relative distributions as shown above By way of example this sets the nondimensional chord to be constant
7. 0 gt 1 gt NSEC wind turbine mode propeller mode not supported in this documentation wind turbine mode tip speed ratio propeller mode advance ratio not supported in this documentation ignore tip loss effects use Prandtl tip loss model Wilson approach PROP code approach ignore hub loss effects use Prandtl hub loss model recommended use classical brake state model use advanced brake state model recommended ignore shaft tilt effects ignore crossflow effects include shaft tilt effects include crossflow effects use flat plate post stall model use Viterna post stall model recommended USEAP 0 gt ignore swirl effects 1 gt include swirl effects recommended WEXP wind boundary layer profile exponent 0 0 is recommended RHO air density lb sec 2 ft 4 slug ft 3 RD rotor radius ft HUB normalized hub radius i e the ratio of hub radius to rotor radius HH normalized hub height i e the ratio of hub height to rotor radius CONE cone angle of the rotor deg BN number of blades NS number of blade segments also ISEG NSEC number of circumferential segments must be gt 4 when WEXP gt 0 IS1 number of the first segment to be used in the analysis usually 1 IS2 number of the last segment to be used in the analysis usually ISEG In the design mode it is reguired that WEXP 0 and NSEC 1 It is recommended that the tip loss models be used and also that th
8. BE_DATA 0 do not printout blade element data SH 0 0 shaft tilt effects RHO 0 0023769 air density slug ft 3 58 Geometry HUB 0 04 normalized hub cutout HH 3 333 normalized hub height BN 3 blade number CONE 6 0 cone angle of rotor deg RD 77 705510 CH_TW 0 145723 6 0000 0 151691 6 4688 0 129292 4 5342 0 107709 11 2173 0 092047 14 9966 0 080868 2 6548 0 072591 1 1105 0 065723 0 0000 0 057635 0 3695 0 039502 0 5392 No stall models used CORRIGAN_EXPN 1 Corrigan inputs are present but not used since stall model is off AIRFOIL MODE 4 4 s814 pd 24 13 3 1 600 6 s814 pd 24 13 3 1 600 6 s812 pd 21 14 33 1 180 6 s813 pd 16 9 3 1 100 6 airfoil family 1 with 4 airfoils r R location and airfoil index AIRFOIL FAMILY 4 0000 1 3000 2 7500 3 1 0000 4 use the first airfoil family the one above USE_AIRFOIL_FAMILY 1 59 Enforce tip loss model to always be on TIPON Use the Prandtl tip loss model not the original modified model TIPMODE 2 Two design points with wind speeds mph that do not change The RPM of both lines is iterated to achieve a fixed TSR of 6 The blade pitch of the first line is iterated for C1 8 The blade pitch for the second DP is not used hence 999 DP 1 17 3030 1 689 16 2 DP 2 32 4432 999 000 30 2 DRY All IDES lines will be ignored until DRY is encountered again below Desired Cl distribution DP 1 1 1 seg
9. JDPRPM where JDPRPM design point for the RPM to use This tipspeed calculation does not include the wind speed component It only includes QR VS MODE Line For variable speed analysis with 2D SWEEP the following line is reguired VS MODE The line should be used one time and placed ahead of the first 2D SWEEP line Two examples are shown below Examples VS MODE PITCH DP 1 WIND SWEEP 5 501 2 TSR SWEEP 9 9 O 2D SWEEP 49 Special lines required for variable speed turbines File wt08a in LCOL45 VS MODE Determine Cp curve PITCH_DP 1 TSR_SWEEP 5 14 25 WIND_SWEEP 16 16 1 2 2D_SWEEP 45 Cp vs TSR WRITE FILES 45 WT NAME Line Wind turbine design files can be given names in the input file by the line WT NAME NAME where NAME is the name of the turbine ZERO TWIST Line In some cases it may be desirable to iterate on the twist along the entire blade span In such instance the twist at the 75 radial station will be adjusted from zero Thus the true blade pitch is the specified blade pitch plus the twist at the 75 station If the converged input data were written out with the DUMP_PROPID line the twist at the 75 station would not be zero Prior to the DUMP_PROPID line the ZERO_TWIST line can be used to zero the twist at the desired station by the line ZERO TWIST RADLOC where RADLOC is the radius location for which the twist is to be zero For example to zero the twist at the 75 stat
10. NEWT2SDDP 100 278 6 1 30 2 25 61 20 15 10 05 111 2 100 75 IDES Oo 0 p W Stage 7 Iterate on chord uniformly to get axial inflow r R 75 333 NEWT1LDP 501 8 333 111 2 999 100 02 IDES Stage 8 Iterate on chord to get axial inflow 9 10 NEWT2SDDP 101 9108 2 1 0 2 0 111 1100 02 IDES Stage 9 Iterate on chord to get axial inflow 2 7 NEWT2SDDP 101 278 6 0 O 0 P W N O O Co o 11 1 100 02 DRY turn off dry run so that the following IDES line will start the iteration IDES Special lines required for variable speed turbines LCOL45 VS_MODE Determine cp curve PITCH_DP 1 TSR SWEEP 5 14 25 WIND_SWEEP 16 16 1 2 2D_SWEEP 45 cp vs TSR WRITE FILES 45 62 Determine the rotor power and thrust curves 2D SWEEP FIXPD 1000 1 PITCH DP 1 TSR SWEEP 6 6 O WIND SWEEP 5 50 1 2 2D SWEEP write out 40 power curve kW vs wind speed mph 51 rotor thrust curve WRITE_FILES 40 51 Obtain aero distributions along the blade 1D_SWEEP PITCH_DP 1 RPM_DP 1 WIND_DP 1 1D SWEEP write out 75 blade 1 d dist 76 blade Re dist 80 blade alfa dist 85 blade cl dist 90 blade a dist it 95 chord dist ft ft 99 twist dist ft deg WRITE_FILES 75 76 80 85 90 95 99 Annual energy production GAEP 16 16 1 45 Report the last GAEP analysis case REPORT_SPECIAL 8 999 999 REPORT_END Write out the rotor design paramet
11. will very rarely happen with running PROPID 7508 When using the post stall models it is reguired that a unigue airfoil file be used for each station For example if the S809 is used along the entire blade then at least two s809 airfoil files must be prescribed in the AIRFOIL MODE line because the stall models will operate on the data depending on the radial location of the airfoils To get even higher fidelity 4 or more stations of the S809 airfoil could be used The post stall models will modify that data for each station 8080 An array limit has been reached when using the relative chord and or twist distributions Too many stations are prescribed 8081 At least two stations must be used with the relative chord and or twist distributions 8082 NS is too large There are too many segments 8083 RAJ MODEL line will not work w MAKE PROPID AFDATA line 9026 Increase nxj2 in gaep f Or lower the number of wind speed values used in the 2D SWEEP line 9027 Increase ngaep in propid inc 9028 Increase nnxj in propid inc This variable is used on the fitness evaluation 9029 Increase naf in the propid inc file 9030 The Corrigan model requires the clmax input for the airfoils given in the AIRFOIL_MODE line Include clmax and the insert angle if the Corrigan model is on 9031 Increase ncmpt in propid inc or reduce icmpt in the ICMPT line 9032 Increase ndp in propid inc or reduce the number of DP lines 9081 The re
12. 11 1842 0 0785 0 1734 0 2490 0 2475 5 5921 0 4489 0 4638 0 4801 0 4831 3 7281 0 2529 0 2695 0 2809 0 2919 2 7960 0 0987 0 1139 0 1257 0 1378 2 2368 0 0388 0 0457 0 0531 0 0613 The first column is the wind speed or TSR the second column is the output for the pitch of 0 deg the third column is the output for the pitch of 1 deg and so on If a RPM sweep is used in the 2D sweep then the TSR for a given wind speed will change for each RPM value However the output for files 45 and 50 only provide one column of TSR values The numbers given in these files are the TSR values corresponding to the last RPM in the RPM sweep Special considerations are required when using TSR SWEEP When TSR SWEEP is used the wind speed must be in mph IXDIM 2 The following example is for a variable speed turbine It is based on the blade and design point from the wt09b run case The pitch is from the first design point the TSR is set to 6 and the wind speed is swept from 5 to 41 mph by 2 25 mph increments The power is capped at 1 MW using the FIXPD line Information on the line FIXPD is found in Chapter 9 The output data files for 40 and 45 are shown below Example 19 LCOL45 VS MODE FIXPD 1000 1 PITCH DP 1 TSR SWEEP 6 6 O WIND SWEEP 5 41 2 25 2 2D SWEEP WRITE FILES 40 45 ftn040 dat 5 0000 4 6462 7 2500 14 2490 9 5000 32 1573 11 7500 60 5494 14 0000 101 9457 16 2500 159 2608 18 5000 234 5046 20 7500 330 8952 23 0000 450 6295 25 250
13. 2D sweep analysis ajaa aa aa aa aa aa AAA kkk k kkk k kkk KK kk Output 56 rotor p vs v gt ftn040 dat rotor cp vs x gt ftn045 dat rotor thrust vs wind speed gt ftn051 dat OAR kk kk kkk kkk kkk A A KK kkk kk Performing 1D sweep analysis gt Done performing 1D sweep analysis KKK K K FK FK FK K K K K K K FK FK FK K K K K K FK K FK FK FK FK K K K K K FK FK FK FK K K K K K K IK K K Output Oe a Ace cre NASN Soto Lr Re ce ch lea Ee eR eae eC blade 1 d dist gt ftn075 dat blade Re dist gt ftn076 dat blade alfa dist gt ftn080 dat blade cl dist gt ftn085 dat blade a dist gt ftn090 dat blade chord ft gt ftn095 dat blade twist ft gt ftn099 dat KKK K K FK FK FK K K K K K K FK FK FK K K K K K FK K FK FK FK FK K K K K K FK FK FK FK K K K K K K K K K determining annual energy Defaults used Weibull shape factor Gamma 2 000 0 886227 Wind speed mph Annual energy kwh yr 16 00 692334 72 kk kk kk kk KK Reporting On kKkkkkKKKK average wind speed mph 16 000 cutout wind speed mph 45 000 aep kWh yr turb 692334 725 geneff 1 000 kk kk kk kk KK KK Reporting Off kkkxxkxkkK 1 2 3 4 5 6 BOCA RK KK KK KK KK kk kk x Writing propid dump file gt ftn021 dat a a aa ajaa aa aa aa aa AR kkk kk aK Warning 450 loobug tt gt airfoil Re lt Re of data somewhere endprog f Warning 451 57 looblg
14. 50 mph in 1 mph increments with the units being mph because IXDIM 2 DP 1 65 1 219 999 2 RPM DP 1 PITCH SWEEP 2 4 1 WIND SWEEP 7 50 1 2 2D SWEEP 13 In addition to a sweep over the wind speed the pitch is now swept over the range from 2 to 4 deg in 1 deg increments The pitch value in the DP line is not used however the rotor speed from the DP line is used The 1D SWEEP line is used to generate data along the blade span such as the blade lift coefficient distribution Preceding the 1D SWEEP line must be lines to set the pitch rotor speed and wind speed to be respectively selected from among the lines PITCH FIXFD FL PITCH DP JDPFL PITCH SWEEP FLS FLF DFL RPM FIXED RPM RPM DP JDPRPM RPM_SWEEP RPMS RPMF DRPM WIND FIXED XJ IXDIM WIND_DP JDPWND WIND SWEEP XJS XJF DXJ IXDIM From each set only one line is used to set the pitch rotor speed and wind speed At most only one sweep line can be used Following these three lines the 1D SWEEP line generates the results that can be written out as discussed in Chapter 7 Example DP 1 65 0000 1 219 999 000 2 DP 2 999 0000 999 000 19 160 2 DP 3 999 0000 999 000 15 000 2 RPM_DP 1 PITCH_DP 1 WIND_DP 3 1D_SWEEP This sequence sets the rotor speed to 65 rpm the pitch to 1 219 deg and the wind speed to 15 mph for analysis The second DP line is not used 6 Input File The input file is assigned in the propid in which contains t
15. 6 version 26 viscosity kinematic VS_MODE 471 49 Weibull shape factor WEXP 6 wind boundary layer exponent 7 wind speed units 12 13 46 wind speed at peak power wind turbine mode 6 WIND_DP WIND_FIXED WIND_SWEEP 13 4 T6H21 451471 49 50 53 WRITE FILES 471 WT_NAME ZERO_TWIST 85
16. Lines NEWT2 lines are used to specify for example the lift coefficient distribution relative to a specified location Such a distribution is referred to as the relative lift coefficient distribution or i This new notation is best introduced through Fig which shows a convenient parameterization of the blade geometry The chord c is composed of the sum of a constant level at the blade root and a chord distribution relative to this constant level that is co Likewise the blade pitch is the sum of the pitch at 75 radius 675 and the twist relative to this point 9 both measured positive in the direction toward feather from the rotor plane In general the chord twist or lift coefficient distributions can be referenced relative to any location as specified by the NEWT2 line To illustrate the approach a fairly sophisticated example is considered A three bladed 9 25 m radius rotor operates at a constant rotor speed of 50 rpm with a fixed pitch of 3 deg at 75 of radius The NREL S814 root S809 primary and 810 tip advanced wind 34 0 00 0 25 0 50 0 75 1 00 Ph ee a fare 0 00 0 25 0 50 0 75 1 00 r Figure 1 Parameterization of blade chord and twist distributions turbine airfoils are used along the blade span Airfoil data for the 814 809 810 series can be obtained through the the National Renewable Energy Laboratory website The blade is defined by 10 segments The design goals are to achieve 1 a specified pe
17. NEWT2 Iteration ISDTP ISCHFD2 1 100 Move Corresponding Chord Independently 2 100 Move Corresponding Twist Independently the pitch of the blade is also unchanged by the present iteration schedule It should be noted that the combined NEWT1 and NEWT2 lines lead to an iteration on 10 variables blade chord offset design point wind speed and eight 0 values for 10 desired output values peak power C at 75 radius and eight C values The current example can be extended to include iteration on the blade chord so that a desired relative axial induction factor distribution can be achieved In particular the example lines NEWT2SDDP 101 3 10 2 8 0 0 0 J O 0 PP W N KE O OO CO CO O o O OO CO Co o o 1 1 2 1 100 0 5 IDES produce a constant axial induction factor from segments 2 through 10 The axial induction factor for a specific blade element can be prescribed with the NEWT1LDP line Doing so together with the relative distribution prescribed as above would then fix the entire axial induction factor distribution for the specified condition After a file is known to reliably converge for all prescriptions all NEWT lines adding these two lines before any iteration will cause the program to automatically converged with out keyboard prompts TOLSP1 TOLSP1 TOLSP2 TOLSP2 where TOLSP1 auto iteration mode convergence tolerance for all NEWT1 lines TOLSP2 auto iteration mode convergence toleran
18. RXJFNT RDXJNT KRDPRPM KRDPFL KRDPXJ REPORT ISWP IRFTP where IRFTP 300 gt peak Power kW 301 gt speed at peak power in mph 302 gt peak Cp 304 gt max torque ft lbs RXJSNT lowest value for wind speed mph in range RXJFNT highest value for wind speed mph in range RDXJNT increment in wind speed mph KRDPRPM design point for rotor speed KRDPFL design point for blade pitch KRDPXJ 999 value is ignored The 1ISWP is modeled after the NEWT1ISWP design line and will run the prop portion of the code again The REPORT_ISWP will report data based on the last analysis performed So whatever is left in the arrays after the previous analysis will be used Similar to the ISWP lines above the local blade characteristics are reported using the following REPORT 1LDP IRFTP RJSEGIX KRDPRPM KRDPFL KRDPXJ REPORT LDP IRFTP RJSEGIX where IRFTP 500 gt local Cl of blade 501 gt local axial induction factor 502 gt local alpha airfoil angle of attack 504 gt local power coefficient 505 gt local power 506 gt local chord cl ft RJSEGIX blade segment for specified parameter KRDPRPM design point for rotor speed KRDPFL design point for blade pitch KRDPXJ design point for wind speed The 1LDP is modeled after the NEWT1LDP design line and will run the prop portion of the code again The REPORT LDP uses the values left in memory A variety of data can be re
19. Selig PROPID notes of 001118 p 1 875 The tolerance for this particular Newton line is either zero or unspecified in which case it is set to zero The Newton line jequ1 is given The solution will not converge in this case What is needed is either a TOLSP1 line or TOL data on the NEWT line 939 An intermediate value in prop f produced a value of 0 or a 78 negative number The value has been forced to a small number in an attempt to continue and find a converged solution inside prop f 940 941 942 943 944 report f 945 This mode is not implement in bemtval called w REPORT BE DATA line 950 LSAF will only accept up to 24 segments The LSAF file will need to be pruned to a smaller number of segments 956 The angle of attack correction computed by the Corrigan model can sometimes be negative This will produce a decrease in cl rather than an increase in cl When a negative value is computed the correction is forced to zero hence no correction is made in this case corgan f A similar routine has been added to dudelta f 957 Selig see menu f 990 Requesting airfoil data and the Reynolds number for a station is zero If this is the root section jseg 1 then this is not a problem It should not happen otherwise 999 This line type is not in the PROPID menu f FEA A CISC ICI ICI ICI CI CI aa akk Kk Kk KK KKK SRI RII 2K FK 2K III IR I aK 2K K K FK KKK KKK KK Errors 1010 PROPID has not been ch
20. area per blade aspect ratio The example also provided information about the last design analysis point used for calcu lations by REPORT_DP_LAST This REPORT line provides the RPM pitch wind speed xj and the tip speed ratio REPORT_DP_LAST assumes that the wind speed is in miles per hour If the calculations were not in mph then the tip speed ratio will not be correct Specific design point information can be provided using REPORT_DP KRDPRPM KRDPFL KRDPXJ where KRDPRPM design point for rpm KRDPFL design point for blade pitch KRDPXJ design point for wind speed If a zero is used that value is ignored Some blade performance information can be reported when using one of the two following REPORT_1IDP IRFTP KRDPRPM KRDPFL KRDPXJ REPORT_IDP IRFTP where IRFTP 200 Power kW 202 Thrust 1b 203 Moment lb ft 204 Omega nondimensional power coef 2 205 Power coef 206 Torque ft lbs 207 Tip speed ft sec 208 Tip speed ratio omega R wind speed KRDPRPM design point for rpm KRDPFL design point for blade pitch KRDPXJ design point for wind speed 24 The 1IDP is modeled after the NEWT1IDP design line see Section B I and will run the prop portion of the code again The REPORT IDP line uses the values from the last analysis point similar to the REPORT DP LAST Peak performance information can be reported using one of the two following REPORT 1ISWP IRFTP RXJSNT
21. data to files 40 power curve kW vs wind speed mph 45 cp vs TSR 51 rotor thrust curve WRITE_FILES 40 45 51 Obtain aero distributions along the blade 1D_SWEEP PITCH_DP 1 RPM_DP 1 WIND_SWEEP 5 30 5 2 1D_SWEEP write out 75 blade 1 d dist 76 blade Re dist 80 blade alfa dist 85 blade cl dist 90 blade a dist 95 chord dist ft ft 99 alfa dist ft deg WRITE_FILES 75 76 80 85 90 95 99 HH H H H Annual energy production GAEP 16 16 1 45 REPORT_START Report the last GAEP analysis case REPORT_SPECIAL 8 999 999 REPORT_END Write out the rotor design parameters to file ftn021 dat DUMP_PROPID 53 The screen output and user interactive input follows aja aa ajaa ajaa aa aa kkk aa kkk kkk kkk kkk k kk k kk Running input file propid in gt wt06a in OR ajaa aa aa aa aa aa aa k kkk KK k kk kkk Reading polar data file pdata f s814 pd Reading polar data file pdata f s814 pd Reading polar data file pdata f s812 pd Reading polar data file pdata f s813 pd newti line 1 prescribed peak power kw 500 at design point rpm 1 pitch 1 adjust size of rotor with step limit 0 300 initial wind turbine design for stage 1 residues for newti equations fnt1 0 1 420 59168 valuei 79 40832 select option 0 stop iteration for current stage number of consecutive iterations 999 to stop execution 99 more options gt gt 0 newti line 2 pres
22. effect will be subseguently issued Warnings can be innocuous but usually they are hints of problems either with the initial input or with the current solution Residues do not go to zero solution does not converge This is an indication that what is specified is not physically possible through an adjustment in the selected input 41 parameters It is suggested that the iteration be done in several stages in order to help deduce the source of the difficulty Physical interpretation of DELTAS and suggested clamp sizes There is no rule of thumb for determining the appropriate clamp size for some problems a clamp may not even be reguired Generally if between successive iterations the residue is reduced and does not switch sign then the clamp can most likely be increased for each variable But if the residue grows for a particular output variable or if the magnitude remains the same but switches sign then the clamp size should be reduced DELTAS is the step size for a given variable for an iteration The clamp is applied to this variable and hence it is necessary to know the physical interpretation of DELTAS Table 4 lists 1 the physical interpretation of DELTAS corresponding to the parameters listed Tables 2 and B and 2 suggested clamp sizes as a starting point Table 4 DELTAS and Suggested Clamp Sizes Keyword DELTAS Clamp Size Scale Rotor Growth 0 20 Rotor Speed A Rotor Speed 5 P
23. pd AFTHK airfoil thickness AFSTALL airfoil stall angle of attack STDELAY stall delay of the airfoil i e where flat plate model starts CLMAXN the clmax of the pd file optional and only required when the Corrigan stall model is used ALINSERT the angle of attack at which to shift the cl alpha data to higher values in the corrigan model optional and only required when the Corrigan stall model is used DUSTART the angle of attack at which the UIUC post stall model starts DUEND the angle of attack at which the UIUC post stall model ends The airfoil data files should follow the examples given by the sample pd file in the runs folder of the archive However a requirement for mode 4 is that the airfoil data must be ordered as a Ci Ca The C and Cy data must extend up to an angle of attack of 27 5 deg in the data files At least two Reynolds number cases should be included to allow for interpolation in the analysis Details regarding the description of the stall parameters AFSTALL and STDELAY can be found in Appendix 10 2 PROPID also implements the Corrigan stall delay model Ref 7 and the UIUC post stall model which are also explained in the Appendix If no stall delay model is being used the C at stall AFSTALL is held constant for the stall delay angle which is read in as the third parameter STDELAY If the Corrigan model is being used then the Cimas CLMAXN for the airf
24. plate 6 Viterna 6 power 18 19 33 B4 45 58 distribution peak power coefficient definition distribution 20 37 peak PRINT INPUT PROP 4 PROP93 propeller mode 6 84 PROPSH l radius hub see hub rotor 7 21 49 RD 6 15 51 59 REPORT_11DP 24H25 GT REPORT_1ISWP REPORT_1LDP REPORT BE DATA REPORT COMMENT REPORT DP 61 REPORT DP LAST 23H24 REPORT END REPORT GEOMETRY REPORT IDP REPORT ISWP 25 REPORT LDP 25 REPORT MD ROFFSET REPORT SEPARATOR REPORT SPECIAL REPORT START P2H231 53 61 REPORT VERSION 26 residue Reynolds number calculation distribution 20 21 RHO 6 15 51 58 RKR GAMMA RNEWT rotor speed see rpm rpm RPM DP 15 14 1619 21 53 163 RPM FIXED RPM SWEEP RPRINT 49 runs directory 4 SH 6 shaft tilt 6 SKIP UNKNOWN WORDS 49 solidity 49 stall angle stall delay angle 73 74 SUMMARY INFO 49 swirl 7 tangential force coefficient distribution thickness distribution 20 RI thrust 181 33 thrust coefficient definition tip loss 6 tip speed 33 tip speed ratio 6 2 13 18 19 45 58 TIPMODE 7 TIPON 7 TIPSPEED 49 tolerance 28 29 BI TOLSP1 40 TOLSP2 A0 torque maximum TSR_SWEEP 45 147 49 twist 36 38 BA KI distribution UIUC post stall model 9 74 USE AIRFOIL FAMILY 11 10 521 59 USEAP
25. power but also distributions like the blade lift distribution and or axial interference factor distribution Such distributions are achievable as long as another distribution is left to be determined that being specifically the blade twist and or chord distributions The method also has multipoint design capabilities For example the blade lift coefficient distribution can be prescribed for one condition while simultaneously the axial induction factor distribution can be prescribed for a different condition In addition the designer can simultaneously specify the peak rotor power constraint which may correspond to yet another condition The PROPSH blade element momentum code 4 which itself is a modified version of the PROP code 5 is used for analysis in the current version of PROPID Desirable features of the code are that it allows for rapid analysis accommodates different airfoil data for each blade element and includes a 3 D post stall airfoil performance synthesization method for better peak power prediction at high wind speed In what follows Chapter 2 discusses typographical conventions used in this manual and also the input file structure The input file is read automatically upon program execution and is assigned in the file propid in which is included in the runs directory of the archive Chapter 3 presents several parameters required for a PROPID design or analysis run Input for the wind turbine operating conditions is prese
26. sensitivities sensitivities sensitivities sensitivities sensitivities sensitivities sensitivities sensitivities sensitivities value2 0 value2 1 value2 1 value2 1 value2 1 value2 1 value2 1 value2 0 value2 0 value2 0 value2 0 value2 0 value2 0 value2 0 value2 0 for for for for for for for for for for for for newti newt1 newt1 newt1 newt1 newt2 newt2 newt2 newt2 newt2 newt2 newt2 design design design design design design design design design design design design 67 clamp2 0 750 90010 deltas2 0 00003 clamp2 0 750 29961 deltas2 0 00005 clamp2 0 750 24981 deltas2 0 00006 clamp2 0 750 19989 deltas2 0 00003 clamp2 0 750 14993 deltas2 0 00007 clamp2 0 750 10015 deltas2 0 00001 clamp2 0 750 05013 deltas2 0 00004 clamp2 0 750 33295 deltas2 0 00000 clamp2 0 020 33297 deltas2 0 00000 clamp2 0 020 33272 deltas2 0 00000 clamp2 0 020 33279 deltas2 0 00000 clamp2 0 020 33282 deltas2 0 00000 clamp2 0 020 33283 deltas2 0 00000 clamp2 0 020 33296 deltas2 0 00000 clamp2 0 020 33295 deltas2 0 00000 clamp2 0 020 parameter para
27. the design point assigned to number JDPFL Instead of using a single pitch the pitch can be swept over a range to generate a family of curves through the PITCH SWEEP line FLS is the initial start value for the pitch FLF is the final value and DFL is the increment Likewise the rotor speed is set by one of the lines RPM FIXED RPM RPM DP JDPRPM RPM SWEEP RPMS RPMF DRPM If the pitch is swept over a range by the line PITCH SWEEP then the rotor speed cannot be swept and visa versa That is either PITCH SWEEP or RPM SWEEP can be used but not both When working with a variable speed turbine VS MODE see Additional Input Lines in Chapter D use tip speed ratio TSR SWEEP TSRS TSRF DTSR instead of any RPM lines Finally the wind speed data is set and the analysis is performed by the lines WIND SWEEP XJS XJF DXJ IXDIM 2D_SWEEP where XJS XJF and DXJ are the initial final and incremental values for the wind speed XJ according to the parameter IXDIM defined in Chapter 4 When using TSR_SWEEP the wind speed must be in miles per hour IXDIM 2 Examples DP 1 65 1 219 999 2 RPM_DP 1 PITCH_DP 1 WIND_SWEEP 7 50 1 2 2D SWEEP In this case the rotor speed and pitch refer to the design point line and are thus set by the values given in the first DP line The value of 999 in the DP line is not used in this example and conseguently it could be anything The wind is swept over the range from 7 to
28. 0 596 2389 27 5000 770 2544 29 7500 975 2075 29 9840 1000 0000 32 0000 1000 0000 34 2500 1000 0000 36 5000 1000 0000 38 7500 1000 0000 41 0000 1000 0000 ftn045 dat 6 0000 0 3832 7 2 1D SWEEP 7 2 1 Available Output Files generated by the 1D SWEEP line are IPRT Data written out to logical unit IPRT 19 blade tip loss function vs nondimensional blade station 60 blade power kW vs nondimensional blade station 61 blade dynamic pressure lb ft 2 vs nondimensional blade station 20 65 blade power coefficient vs nondimensional blade station 75 blade airfoil lift to drag ratio vs nondimensional blade station 76 blade Reynolds number vs blade station ft 80 blade angle of attack deg vs nondimensional blade station 84 blade drag coefficient vs nondimensional blade station 85 blade lift coefficient vs nondimensional blade station 86 blade Cl c lift coefficient chord ft vs nondimensional blade station 87 blade normal force coefficient Cn vs nondimensional blade station 88 blade tangential force coefficient Ct vs nondimensional blade station 90 blade axial induction factor vs nondimensional blade station 94 blade nondimensional chord chord radius vs nondimensional blade station 95 blade chord ft vs blade station ft 96 blade t c distribution vs blade station ft 97 blade thickness inch vs blade station ft 99 blade twist deg vs blade station ft 100 blade twist deg vs nondimensional blade station
29. 22 check f 1062 Post stall start angle must be less than the stall angle 1501 When using the GAEP line the WRITE FILES line must be used to write out the power curve WRITE FILES 40 before the GAEP line 1950 LSAF accepts 24 radius points but there are more than 24 after the PRUNE line was used in an attempt to reduce the number of points below the 24 max limit 1951 PRUNE points may be in descending order from tip to root 1952 That flap loads case does not exist 3020 ichord gt nchord or itwist gt ntwist 3021 ichord gt nchord or itwist gt ntwist 4051 Must use mph in the DP line when using the RPM FIXED ON TSR line 5000 The generator efficiency is greater than 1 This is an error since the efficiency should always be less than 1 5055 5056 An IDES line is required after all of the basic defining parameters and before the analysis lines This IDES line is needed because the predes f subroutine might be needed to perform some operations before the analysis Also the IDES line will run the check f subroutine 6050 Not a valid mode for use with ALFA MIN MAX INC line 6071 To use the post stall models the airfoil data files pd must be used The PROP format for the airfoil data will not work 7010 prop f did not converge after a set number of iterations set by 80 the line iterprop What this means is that the blade geometry is rather unusual This can sometimes happen when running PROPGA It
30. 4 ftn files 011 27 48 014 15 019 020 I8 021 27 BJ 022 039 040 045 8H20 471 50 53 050 18 19 051 060 061 065 075 20 53 076 080 082 084 085 20H22 53 086 PO 087 088 090 094 PO PT 095 20H22 53 83 096 097 099 100 format 18 RI GAEP 46 efficiency see generator efficiency gaep dat 27 gearbox efficiency see generator efficiency generator efficiency 27 46 HH 6 hub height 7 radius 7 HUB 6 15 5159 hub loss 6 HURRICANE_SPECS 46 TBR 6 15 51 58 IDES 12 16 29 BI 5 36 38 KO 45 8 INCV 6 1S1 6 182 6 15 51 58 ISTL 6 ITERMAX 47 ITERPROP 47 LCOL45 47 LHUB 6 lift coefficient distribution 20 28 BA 351 37 B3 A1 lift to drag ratio distribution 20 LTIP 6 MODE 6 15 51 58 moment 33 NEWT1 NEWT1IDP 33 52 60 61 200 33 202 33 203 33 205 206 33 207 NEWT1ISWP 300 301 302 28 304 NEWT1LDP zo 500 501 502 BA 504 505 506 NEWT2 31 BA NEWT2SDDP 30 37 B9 511 6A 100 37 38 101 40 102 104 105 B7 normal force coefficient distribution 20 NS NSEC 6 PAUSE 47 pitch 12 19 22 KI 5 49 PITCH_DP 12 14 16 17 20 21 45 27 49 PITCH FIXED PITCH SWEEP 12 A 18 19 post stall 73 post stall model 74 post stall model flat
31. ATA The second source is the input data and is from the input line PRINT INPUT More information on the input lines is found in Chapter 9 7 4 3 ftn021 dat ftn022 dat This output file contains the converged blade data It is created from either DUMP PROPID or DUMP PROP93 See Section 8 1 7 4 4 GAEP data The gaep dat file contains the results of the gross annual energy production calculations initialized by the input line GAEP See Chapter 9 for more information The generator gearbox efficiency curve data is written to ftn015 dat when WRITE FILES 15 is used This file contains the efficiency value from the GAEP input line versus the wind speed The data in this file will only extend to the cutout wind speed used on the GAEP line The results for this file will only be computed with the GAEP line so the WRITE FILES 15 must be after the GAEP line The WRITE FILES should also appear before any 1D SWEEP lines in order to write out all the wind speeds in the ftn015 dat file 27 7 4 5 C Ca and a data out of the code It is possible to extract aerodynamic data at each radial station from the results of the code Examples on how this is done can be found in the companion propid doc txt file and in the wt02a wt03a and wt07a examples in the runs directory 8 Design Mode The design mode can be used to specify a desired output that is achieved by automatically adjusting one of the inputs If a single value is specified e g peak rot
32. IMDP IDP 0 gt XJDP IDP is wind speed ft sec 1 gt XJDP IDP is wind speed m sec 2 gt XJDP IDP is wind speed mph 3 gt XJDP IDP is tip speed ratio In the input file these conditions are later referred to by their design point number IDP above An alternative to entering the rotor speed blade pitch and wind speed for use in analysis is discussed in Chapter 5 5 Analysis Mode The analysis mode in the code is used to determine the rotor performance via the 2D_SWEEP line and blade aerodynamic characteristics via 1D SWEEP line both of which must be preceded by lines that set the conditions The data generated by the 2D SWEEP and 1D SWEEP lines are stored in memory until the WRITE FILES line is issued to write out the data to an ASCII file see Chapter 7 The 2D SWEEP line is used to determine the rotor performance characteristics such as the power curve vs wind speed power coefficient vs tip speed ratio etc Moreover a family of curves can be generated for different values of pitch rotor speed or tip speed ratio Prior to any analysis initialization of various parameters is reguired by issuing the single line IDES Next the blade pitch is set by using one of the following lines PITCH FIXED FL PITCH DP JDPFL PITCH SWEEP FLS FLF DFL 12 The PITCH FIXED line sets the pitch to the value of FL deg or the PITCH DP line sets the pitch to the value given by one of the DP lines in particular
33. Model for Stall Delay Due to Rotation for HAWTs American Wind Energy Association WINDPOWER 1997 Conference Austin TX 1997 72 NO WARRANTY The author and the University of Illinois make NO WARRANTY or representation either expressed or implied with respect to this software its guality accuracy merchantability or fitness for a particular purpose This software is provided AS IS and you its user assume the entire risk as to its guality and accuracy Appendix A Stall Angle Stall Delay Angle and Re lated Angles Foreword The following describes the reasons and conventions for the various angles used in defining the airfoil data in PROPID Mode 3 and 4 Discussion In all of the following figures points A B C etc will denote points on the lift curve The solid black line is the original lift curve The red curve indicates that a parameter has been modified and the resulting lift curve has been generated The black dotted lines are used to locate points on the curves Figure 6 shows the basic approach taken in defining the C a curve in PROPID The data input to PROPID via the pd file is indicated by the points A B C E The lift curve generated by PROPID is A B C D The stall angle at point B is specified by the user The stall delay angle B C is also user defined If no post stall models are on PROPID adds the stall delay angle to the stall angle and holds the cl constant over that range taking the constan
34. P 1 WIND_SWEEP 5 30 5 2 1D_SWEEP write out 75 blade 1 d dist 76 blade Re dist 80 blade alfa dist 85 blade cl dist 90 blade a dist WRITE_FILES 75 76 80 85 90 Write out 95 chord dist ft ft 99 alfa dist ft deg WRITE_FILES 95 99 Write out the rotor design parameters to file ftn021 dat DUMP PROPID The WRITE_FILES line will be discussed in Chapter 7 7 Output Files Results generated by the 2D_SWEEP and 1D_SWEEP lines can be written to ASCII files by the line WRITE FILES IPRT 1 IPRT 2 IPRT 3 sui IPRT 20 17 Example DP 1 65 1 219 999 2 RPM_DP 1 PITCH_SWEEP 2 4 1 WIND_SWEEP 7 50 1 2 2D_SWEEP WRITE_FILES 40 45 The lines above analyze a rotor and then the WRITE_FILES line writes to ASCII files the power vs wind speed ftn040 dat and power coefficient vs TSR ftn045 dat generated by the preceding 2D SWEEP line 7 1 2D SWEEP 7 1 1 Available Output Files generated by the 2D SWEEP line that can be subsequently written out are listed below IPRT Data written out to logical unit IPRT 20 torgue ft 1b vs wind speed 39 RPM vs wind speed 40 rotor power kW vs wind speed 45 rotor power coefficient vs TSR If VS MODE is used then power coefficient vs wind speed If VS MODE and LCOL45 are used then back to power coef vs TSR See Additional Input Lines 50 rotor thrust coefficient vs TSR If VS MODE is used then thrust coefficient vs wind spe
35. PROPID User Manual Version 5 3 1 Aerodynamic Design Software for Horizontal Axis Wind Turbines Michael S Selig et al UIUC Applied Aerodynamics Group Department of Aerospace Engineering University of Illinois at Urbana Champaign Urbana IL 61801 Last updated January 6 2012 Copyright 1993 2011 Michael S Selig All rights reserved Contents 2 Reading this User Manua 3 Required Data for Design and Analysis Modes 3 1 Basic Setup Parameter OT 8 1 NEWTI Line 8 2 NEWT2 Line 0 1 0 0 12 10 Annotated Examples 10 1 Stall Regulated 10 2 Variable Speed Index 72 73 73 77 83 1 Overview PROPID is a computer program for the design and analysis of horizontal axis wind tur bines I The unique strength of the current design method is its inverse design capability For instance the current method allows the designer to specify directly the peak power for a stall regulated rotor The iterative inverse solver is then used to adjust one of the user selected inputs so that the desired peak rotor power is achieved More generally the method permits the designer to specify several performance characteristics as long as an equal number of input parameters are allowed to be automatically adjusted by the iterative inverse method The approach is based on similar inverse design methodology for airfoils and cascades 2 3 PROPID not only allows for the specification of single variables like peak
36. RSPT2 15 1 2 3 ISEG JPT blade section drag coefficient at blade station IRSPT2 The version number of PROPID can be reported using REPORT_VERSION Different blade element momentum theory BEMT information can be reported using REPORT BE DATA IBEMT RADLOC2 where IBEMT RADLOC2 14 gt chord normal force 15 gt chord tangential force 16 gt dynamic pressure radial position 26 The radial position RADLOC2 can be any value between 0 hub and 1 tip The bending moment can also be reported not at the hub but outboard by an offset by using REPORT MD ROFFSET roffset where ROFFSET is the normalized radial offset The root bending moment is assumed to be due to a single force at the 75 blade station This force is used to calculate the moment at the offset location 7 4 Additional Output Files Besides the output files from the 2D and 1D sweeps PROPID can produce some additional output files 7 4 1 Airfoil blending values The airfoil blending values see Section B 3 are written to ftn014 dat when WRITE_FILES 14 is used The output file contains four columns of data where the first is the radius station the second is the blending distribution values the third is the airfoil weighting values and the fourth is the airfoil thickness ratio 7 4 2 ftn011 dat This output file can contain data from two sources The first source is the blade element performance data and is from the input line BE D
37. a new design problem since convergence can sometimes be difficult in which case clues can be gleaned from the convergence history The following output is echoed to the screen ROR I RR ak ak ak ak ak aK K K K 2K ajaa ajajaa aak ak 2K 2K ak ak RK KK KK KK KK SKK K K Running input file propid in gt wt05c in kkk k ak ak ak ak K aK K K K 2K 3K 3K 3K 3k K KK KK KK KK K K Reading polar data file pdata f s814 pd Reading polar data file pdata f s814 pd Reading polar data file pdata f s812 pd Reading polar data file pdata f s813 pd newti line 31 1 prescribed peak power kw 95 at design point rpm 1 pitch 1 adjust pitch 1 with step limit 1 500 deg initial wind turbine design for stage 1 residues for newti equations fnt1 0 1 15 59168 valuei 79 40832 select option 0 stop iteration for current stage number of consecutive iterations 999 to stop execution 99 more options gt gt 2 in consecutive iteration mode iteration 1 calculating sensitivities for newtl design parameter 1 residues for newti equations fnti_1 1 5 90454 valuei 89 09546 deltasi 1 50000 clamp1 1 500 iteration 2 calculating sensitivities for newtl design parameter 1 residues for newti equations fnti_1 1 0 43994 valuei 94 56006 deltasi 0 77385 clamp1 1 500 select option 0 stop iteration for current stage number of consecutive iterations 999 to stop execution 99 more options
38. ak power of 75 kW and 2 a desired lift coefficient distribution at a wind speed yet to be determined As previously discussed one means of achieving the desired peak power is to adjust the solidity via the blade chord offset co as shown in Fig P by the lines DP 1 50 0 2 5 999 2 DP 2 999 999 14 444 2 NEWT1ISWP 300 75 20 35 1 111 2 999 100 IDES Continuing with the current example the desired lift coefficient distribution is shown in Fig As with the blade twist distribution it is convenient to divide the desired C distribution into two components Ch sy G This C distribution corresponds roughly to the maximum L D condition of the airfoils along the blade span The speed corresponding to this C distribution is defined in part by the peak power level for the following reason As shown in Fig P the peak rotor power is reached at a wind speed near 13 41 m sec 30 mph At this speed the rotor C distribution is nearly centered about the Cimas of the airfoils along the span Likewise near the cut in speed of 4 47 m sec 10 mph the net C distribution is slightly above zero lift Thus it would be inconsistent to specify that the desired C 35 0 25 C 0 00 0 00 0 25 0 50 0 75 1 00 r 100 x 5 50 a 5 5 FE 0 0 5 10 15 Vind Speed m s Figure 2 Adjustment of blade chord offset to achieve desired peak power distribution should occur at a wind speed near 13 41 m sec 30 mph or near the cut in speed I
39. alldelay re E D Flat plate model Osan Ostan stanidetay Q Figure 6 Description of basic angles stall angle and stall delay angle at point C Note that for the case shown the stall delay angle B C is increased over that used in Fig 7 The flat plate model starts for angles higher than stall stall delay In developing the code this approach was taken so that the effects of a lower Crna could be rapidly modeled by simply changing the user prescribed stall angle of attack B Figure 9 shows among other cases the approach to take when the entire stall behavior is known and represented in the tabulated airfoil data given in the pd file First A B C shows the Cr a data known from experiment At the stall angle C the flat plate model begins and extends the curve to point D and then to higher angles not shown To initiate the start of the flat plate model at point C the stall delay angle has been set to zero This approach is the prefered approach when the stall data is known and representative of the airfoil behavior on the blade Two other cases are also shown to illustrate and amplify the effects that the various angles can have First if the stall angle is set at point B and a non zero stall delay angle is used the clmax is set to that value at point B and held to point B C If on the other hand the stall delay angle is set to zero point C moves to C and the flat plate model then b
40. alue for CLAMP1 can be left unspecified in the NEWT1 line In this case the value TOL1 must be unspecified as well The parameter TOL1 is used in the convergence test and is the desired difference between the current value and the specified value for the output parameter If iteration is to proceed automatically until convergence without user input then TOL1 must be specified for use in the convergence test In this case all NEWT1 and NEWT2 lines must contain values for TOL1 and as later discussed TOL2 if a NEWT2 line is used If TOL1 is not specified then the iteration steps are performed interactively Interactively monitoring convergence is useful for debugging cases when convergence is not easily achieved After any number of NEWT1 and NEWT2 lines the iteration is initiated by the IDES line Anytime the IDES line is issued the iteration scheme will attempt to achieve the desired specifications for all the NEWT1 and NEWT2 lines that preceded the current IDES line Once convergence is achieved more NEWT1 and NEWT2 lines can be used and the IDES can be issued again to converge the solution to all the preceding specifications Example 29 DP 1 64 2 00 15 000 2 NEWT1ISWP 300 95 25 501 11 999 131 1 5 0 1 IDES For this example the peak rotor power is specified to be 95 kW over the wind speed range from 25 mph to 50 mph in increments of 1 mph The corresponding rotor speed and pitch are 64 rpm and 2 deg respectiv
41. alue must be 0 A spline is fit through the blend distribution values A method to determine the blending distribution is as follows First set the blend distribution in the AIRFOIL_FAMILY lines Then plot the thickness distribution and the blend distribution to see if it makes sense i e looks smooth These values are written to ftn014 dat see Section 7 4 1 In general a smooth thickness distribution will be obtained if the blend function is weighted according to the airfoil thickness distribution If no values are given for BLENDDST PROPID assumes that the blend function is 1 AFX This blending is the same as linearly interpolating between the airfoil locations The linear distribution is recommended for most cases The following examples show two blending distributions The first is linear with respect to the blade radius station This distribution is the same as the default distribution if no BLENDDST values are given in the AIRFOIL_FAMILY lines The second example shows a blend distribution weighted by the airfoil thickness distribution Both examples give the blade radius station the airfoil thickness ratio and the blend distribution values BLENDDST Example 1 radius thickness BLENDDST 0 00 0 24 1 00 0 30 0 24 0 70 0 75 0 18 0 25 1 00 0 16 0 00 10 Example 2 radius thickness BLENDDST 0 00 0 24 1 00 0 50 0 21 0 25 1 00 0 20 0 00 More than one airfoil family can be defined in one PROPID input file They are num be
42. at 0 0911 and zero blade twist These values are relative to the root and the coordinate pair 0 0 assumed CHORD BASE 0 0911 CHORD RELATIVE 2 0 5 0 1 0 0 TWIST_RELATIVE 2 0 5 0 1 0 0 CLLOSS Line To model the lift loss or increase due to roughness the CLLOSS line can be used CLLOSS CLLOSS 1 CLLOSS 1SE0 The values CLLOSS 1 through CLOSS ISEG one for each blade segment are the amount loss in Cima For example use a value of 0 14 for a 14 loss in Chas For an increase use a negative value 44 DRY Line Sometimes it is useful to have PROPID echo to the screen the desired NEWT1 and NEWT2 line prescriptions without performing the iteration usually prompted by the IDES lines To only show the prescriptions as a check on the input file use the line DRY to toggle on and off any following IDES lines For example if two DRY lines are used the first will turn off all of the following IDES lines until the second DRY line is reached ECHO INPUT Line To echo the input lines from the input file to the screen use the following line ECHO INPUT FIXPD Line For variable speed wind turbine operation the power can be cropped at the rated power of the wind turbine using FIXPD FIXPD ITEST where FIXPD rated power of the wind turbine in kW ITEST 1 gt fill in the corner of the power curve between normal operation and the maximum power cropped value Adds one point to the pow
43. ata must span the blade length 9802 When using the TWIST_RELATIVE line the first and last values in radius should be 0 and 1 respectively So the data must span the blade length 9999 This line is not in the PROPID dictionary as a valid line type This error can be suppressed by using the line SKIP_UNKNOWN_WORDS which is a toggle menu f FEA AAA A K K aK K aK aK aK ak IR 3k 3k 3K 3K 3K I 3K aa 21 21 21 21 21 21 2 ajaa 3K 3K 3K 3K 3K 3K A AC AC ACCA EKK KK SK 3K 3K 3K 3K 3K K K K 82 Index 1D SWEEP 22 air 7 2D SWEFP I2H14 6H20 43 451471 491 design point 62 63 advance ratio 6 airfoil blending ZOHO 27 airfoil data BHII AIRFOIL_FAMILY AIRFOIL MODE angle of attack distribution 20 37 area 49 aspect ratio 24 49 ATOL axial induction factor distribution 20 37 20 BE DATA BEEP blade number 7 blade segments 7 BN 6 brake state 6 BUMPALPHA BUMPCD 13 BUMPCL 23 CALC_LOADS 46 CDFAC AA CH_TW 7 chord distribution CHORD BASE 7 AA ce distribution 20 22 clamp 28 29 BI 33 42 CLLOSS 44 CONE 6 cone angle 7 Corrigan stall delay model DHIOL 74 CORRIGAN EXPN 91 15 51 59 density DP drag coefficient distribution BO DRY DU stall model see UIUC post stall model DUMP_PROP93 DUMP_PROPID dynamic pressure distribution 20 ECHO_INPUT figure of merit FIXPD flat plate model 7
44. ce for all NEWT2 lines 40 8 3 General Tips Selecting suitable input variables for iteration When selecting input variables for iteration convergence is most rapidly achieved when the specified output variable depends strongly on the selected input variable For instance peak power is a strong function of solidity blade pitch and rotor speed but peak power is a weak function of cone angle for all practical purposes Some specific suggestions are in order If the relative lift is specified then convergence is best achieved through iteration on the blade twist If the axial induction factor is prescribed convergence is best achieved through iteration on the blade chord Under specification of variables for iteration Care should be taken to ensure that an input variable is not selected for iteration more than once There are no special checks in the code should this happen by user error i e inadvertently occur Specifying the same variable twice for iteration is equivalent to not specifying enough variables for iteration While the program may run it will not converge Specified lift coefficient distribution If the lift coefficient is specified along the span the lift coefficient should not of course exceed the local maximum lift coefficient of the airfoil since such specification would not be physically possible i e achievable during iteration Moreover a problem can occur when the specified C distribution is t
45. cribed tip speed 220 0000 at design point rpm 1 pitch 1 xj xx adjust rpm 1 with step limit 0 000 rpm initial wind turbine design for stage 2 residues for newti equations fnti 0 1 420 59168 value1 fnt1 0 2 55 06220 valuei 79 40832 164 93780 select option 0 stop iteration for current stage number of consecutive iterations 999 to stop execution 99 more options 54 gt gt 6 in consecutive iteration mode iteration 1 calculating sensitivities for newtl design parameter 1 calculating sensitivities for newtl design parameter 2 residues for newti equations fnti_1 1 329 09534 valuei 170 90466 deltasi 0 30000 clamp1 0 300 178 79306 deltasi x fnti_1 2 41 20694 value1 iteration 2 calculating sensitivities for newtl design parameter 1 calculating sensitivities for newtl design parameter 2 residues for newti equations fnt1 1 1 149 57228 value1 350 42772 deltas1i 0 30000 clamp1 0 300 190 62873 deltasi 9 59874 fnti_1 2 29 37127 value1 iteration 3 calculating sensitivities for newtl design parameter 1 calculating sensitivities for newtl design parameter 2 residues for newti equations fnti_1 1 8 00111 valuei 491 99889 deltasi 0 03103 clamp1 0 300 fnti_1 2 2 52905 valuel 217 47095 deltasi 7 76284 iteration 4 calculating sensitivities for newtl design parameter 1 calculating sensit
46. e 1 which is the original method used in the PROP code begin airfoil data AIRFOIL_MODE 1 1 MM 1 NN 1 first segment AL 1 CL 1 CALCMM 1 1 CLCMM 1 AD 1 CD 1 AD NN 1 CD NN 1 ISEC MM JSEG NN JSEG intermediate segment AL JSEG CL JSEG ALCMM JSEG CLCMM JSEG AD JSEG CD JSEG AD NN JSEG CD NNCJSEG ISEC MM ISEG NN ISEG last segment AL ISEG CL ISEG AL MM ISEG CL MM ISEG AD ISEG CD ISEG AD NN ISEG 1 CD NN ISEG end AL and AD are the angles of attack deg corresponding to the lift and drag coefficients CL and CD respectively MM JSEG and NN JSEG are the number of a C and a Ca pairs to follow for segment JSEG No more than 20 a C and a C4 pairs can be used for a given segment The most common airfoil input method is mode 4 which includes more options related to stall delay The format of the data is as follows AIRFOIL MODE 4 airfoil data is in order of alfa cl cd IAF AFFILE 1 AFTHK 1 AFSTALL 1 STDELAY 1 CLMAXN 1 ALINSERT 1 DUSTART 1 DUEND 1 AFFILE JAF AFTHK JAF AFSTALL JAF STDELAY JAF CLMAXN JAF ALINSERT JAF DUSTART JAF DUEND JAF AFFILE 14F AFTHK IAF AFSTALL IAF STDELAY IAF CLMAXN IAF ALINSERT IAF DUSTART IAF DUEND IAF where AFFILE airfoil file name
47. ecked to work in propeller mode It probably will not work correctly 1020 The prop f code did not converge to a proper solution and this can likely be seen in the cl or axial induction factor distribution for the segment noted in the screen dump regarding the error The solution is to use the RELAXF line with a factor less than 1 With a factor less than 1 suggested 0 6 relaxation will be applied to the value dct used in the iteration loop for a blade segment The smaller the relaxf value the more iterations and longer the run times The only advantage to using this factor is to get a solution it does not speed up the solution or create a better solution If no Error 1020 message is given then the solution has converged This error is likely only to appear with running in TIPMODE 2 Prandtl model only as opposed to the Wilson Prandtl model a modified Prandtl model and not as accurate 79 1030 The first blend value must be 1 and the last must be 0 Check the AIRFOIL FAMILY line 1031 The first blend value must be 1 and the last must be 0 Check the AIRFOIL FAMILY line 1032 In the AIRFOIL FAMILY line an airfoil index is specified greater than the number of airfoils included in the AIRFOIL MODE line For example 3 airfoils were input through the AIRFOIL MODE line and the AIRFOIL FAMILY line specified using airfoil index 4 i e the AIRFOIL FAMILY line used greater than 3 1060 1061 Corrigan data checks Same error as 93
48. ed gt ftn051 dat OC aa aa k kkk kk kk KK kk kk k kk Performing 1D sweep analysis gt Done performing 1D sweep analysis KKK K K FK FK K K K K K K K FK FK FK FK K K K K FK K FK FK FK FK K K K K K K FK FK FK 3K K K K K K K K K Output ly aa the ta An na A AA N Ann in Nna o J RE oo blade 1 d dist gt ftn075 dat blade Re dist gt ftn076 dat blade alfa dist gt ftn080 dat blade cl dist gt ftn085 dat blade a dist gt ftn090 dat blade chord ft gt ftn095 dat blade twist ft gt ftn099 dat KKK K K FK FK FK K K K K K K FK FK FK FK K K K K FK K FK FK FK K K K K K K FK FK FK KK K K K OK KK K K determining annual energy Defaults used Weibull shape factor Gamma 2 000 0 886227 Annual energy kwh yr 2175948 18 Wind speed mph 16 00 16 000 45 000 aep kWh yr turb geneff 2175948 184 1 000 KKKKKKKKKKKKK Reporting Off KK kk kk kk kk KKK K K FK FK K K K K K K K FK FK FK FK K K K K K K FK FK FK FK K K K KK KK KK KK K K K K 71 13 14 15 16 17 Writing propid dump file gt ftn021 dat kk k ak ak ak ak K ak K 3K 2K 2K 3K 3K 3K 3K 3K 3K aK 2K 2K 2K 2K K K I I K KKK KKK KKK Warning 450 loobug tt gt airfoil Re lt Re of data somewhere endprog f Warning 451 looblg tt gt airfoil Re gt Re of data somewhere endprog f OC k k kkk kk kk kkk kk kkk kk kkk kk kk k kk PROPID Successful run x Closing input file pro
49. ed 51 rotor thrust 1b vs wind speed For wind turbines the power coefficient Cp and the thrust coefficient Cr are defined as JP Si 5PU3A T o 5PUPA where p is the air density U is the wind speed and A is the swept area A 7 x radius 7 1 2 File Format Each data case is written to its own individual ASCII file with the name ftn dat where xxx is the IPRT number listed earlier Results are presented in column format in each file The first column are the wind speed or TSR for 45 and 50 values given in the WIND SWEEP line in the units specified in that line The special considerations necessary when using 18 TSR SWEEP will be discussed later The rest of the columns present the output with one column for each value in the second sweep if it is used Example RPM_DP 1 PITCH_SWEEP 0 3 1 WIND_SWEEP 10 50 10 2 2D_SWEEP WRITE_FILES 40 45 This example uses the blade and design point from the wt01a run case In this example the RPM is from the first design point the pitch is swept from 0 to 3 deg in 1 deg increments and the wind is swept from 10 to 50 mph in 10 mph increments The rotor power and power coefficient are written to their respective output files Examples of the output files follow ftn040 dat 10 0000 0 7635 1 6874 2 4225 2 4086 20 0000 34 9396 36 0997 37 3726 37 6072 30 0000 66 4508 70 7967 73 7919 76 6791 40 0000 61 4906 70 9003 78 2722 85 8334 50 0000 47 1642 55 6055 64 5448 74 5089 ftn045 dat
50. egins at point B C Thus it is quite important to understand the meanings of these angles and to set them appropriately Figure shows the data generation when using UIUC post stall model First it is important to note that the post stall models can be used with stall delay and the models build the 3D data based on the 2D data as partly defined by the stall and stall delay angles In the case of the Corrigan model the lift curve A E F G will follow the shape of the input 2D lift curve A B C D exactly this is not the case shown The Corrigan stall curve though stalling at a higher angle follows the 2D curve because the 3D data is generated by simply adding a constant increment to the 2D stall curve past the insert angle followed by a shift to the right so that the lift curve is continuous In the UIUC model point F the end angle is specified as desired The start angle point E is also user prescribed The flat plate model then extends from point F to point G and beyond 74 p D Flat plate model Ostan O stalkdelay Catal Figure 7 The effect of changing the stall delay angle XStalldelay a Cc 1 I 1 ws tall stant Stalidelay Figure 8 The effect of changing the stall angle 75 G stalldelay 10 DYK Flat plate model stall Start Fstalldelay Figure 9 Various uses of the stall delay angle and the prefered approach when given the experimen
51. ely To achieve the desired peak power the blade pitch is iterated and has a clamp of 1 5 deg Iteration will be performed automatically until the actual peak power is within 0 1 kW of the desired peak power of 95 kW For this example the following output is echoed to the screen BOO aa aa ajaa k kkk kkk kkk kkk kkk k kk KK KK kk k k k Running input file propid in gt wt05b in OAR kkk k kkk kkk kk kkk kk kkk kk Reading polar data file pdata f s814 pd Reading polar data file pdata f s814 pd Reading polar data file pdata f s812 pd Reading polar data file pdata f s813 pd newti line 1 prescribed peak power kw 95 at design point rpm 1 pitch 1 adjust pitch 1 with step limit 1 500 deg initial wind turbine design for stage 1 residues for newti equations fnt1 0 1 15 59168 valuei 79 40832 iteration 1 calculating sensitivities for newtl design parameter 1 residues for newti equations fnt1_1 1 5 90454 valuei 89 09546 deltasi 1 50000 clamp1 1 500 finished iteration 1 iteration 2 calculating sensitivities for newtl design parameter 1 residues for newti equations fnt1_1 1 0 43994 valuei 94 56006 deltasi clamp1 0 77385 1 500 finished iteration 2 30 iteration 3 calculating sensitivities for newtl design parameter 1 residues for newti equations fnt1 1 1 0 00362 valuei 95 00362 deltasi 0 07284 clampi 1 500 finished iteration 3
52. er curve and thus determines the exact wind speed for rated power If no arguments are given the previous FIXPD line is turned off When using FIXPD only one TSR or pitch can be used in the 2D_SWEEP Therefore only the wind speed can be swept Example FIXPD 500 1 PITCH_DP 1 TSR SWEEP 6 6 O WIND SWEEP 5 50 1 2 2D SWEEP write out 40 power curve kW vs wind speed mph 51 rotor thrust curve WRITE_FILES 40 51 45 GAEP Line Gross annual energy production GAEP can be determine using GAEP GVMIN GVMAX GVINC GVCUT GENEFF where GVMIN min average wind speed GVMAX max average wind speed GVINC wind speed increment GVCUT cutout wind speed GENEFF generator efficiency default is 1 The GAEP line must appear after the 2D SWEEP line since the GAEP calculation uses the re sults from the sweep Units for the wind speeds are the same as those used in the WIND SWEEP for the 2D SWEEP So if the wind speeds in the WIND SWEEP were in ft sec IXDIM 0 then the GAEP wind speeds must be in ft sec Reminder that when the TSR SWEEP is used the wind speeds must be in mph IXDIM 2 The unit for GAEP is kW hr Example GAEP 16 16 1 45 Results are written to the file gaep dat HURRICANE Lines The hurricane specs are set using HURRICANE_SPECS VMAX HURRI CDMAX HURRI where VMAX HURRI wind speed ft sec CDMAX HURRI drag coefficient This is the load per segment per one blade The l
53. ers to file ftn021 dat DUMP_PROPID The screen output and user interactive input follows KAKKKKKKKKKKKKKKKKKKKKKKKKKKKKKKKKKKKKAKKKKK KK Running input file propid in gt wt09b man in aa aa ajaa ajaa a aa a aa aa kkk kk kkk kkk kkk KK kkk kkk 63 Reading polar data file pdata f s814 pd Reading polar data file pdata f s814 pd Reading polar data file pdata f s812 pd Reading polar data file pdata f s813 pd dry run turned on newti line 1 prescribed tip speed 140 8000 at design point rpm 1 pitch xj 1 adjust rpm 1 with step limit 0 000 rpm newt1 line 2 prescribed tip speed 264 0000 at design point rpm 2 pitch xj 2 adjust rpm 2 with step limit 0 000 rpm KAKKKKKKKKKKKA Reporting On XKKXKKKKKK 1 blade rpm 1 17 303 2 blade pitch 1 deg 1 689 3 blade xj 1 16 000 4 tip speed ft sec 140 800 5 tip speed ratio 6 000 6 ttr Sy TN KA san 7 blade rpm 2 32 443 8 blade pitch 2 deg 999 000 9 blade xj 2 30 000 10 tip speed ft sec 264 000 11 tip speed ratio 6 000 12 newti line 3 prescribed power kw 1000 at design point rpm 2 pitch 1 xj 2 adjust size of rotor with step limit 0 000 newti line 4 prescribed cl 8 1 00 at design point rpm 1 pitch 1 xj 1 adjust pitch 1 with step limit 0 750 deg newt2 line 1 prescribed cl dist from 9 to 10 relative to 8 at design point rpm 1 pitc
54. ey be enforced for all conditions using the single line TIPON This TIPON line can turned on used at any point before doing the first analysis Another option replaces the original prop f tip loss model with that defined originally by Prandtl with the additional line TIPMODE 2 This TIPMODE 2 line can turned on used at any point before doing the first analysis 3 2 Blade Geometry The CH TW line is used to enter the chord and twist distributions from root to tip begin chord and twist data CH TW CH 1 TW 1 root chord and twist CH JSEG TW JSEG CH ISEG TW ISEG tip chord and twist end where CH is the normalized blade chord i e the ratio of the blade chord to the rotor radius and TW is the blade twist angle deg The chord and twist may also be defined relative to base values e g by using the CHORD BASE group of lines but this approach is not often used see Ref 6 The blade station for the first chord and twist given with CH_TW is at 1 station 1 The following blade stations are then at every TSE For ten blade segments the blade stations would then be 0 050 0 150 0 250 0 350 and so on until 0 950 3 3 Blade Airfoil Data The AIRFOIL MODE line initiates the input of the airfoil a C and a Cy data for each blade segment There are three standard input mode types 1 3 and 4 The preferred mode is type 4 Nevertheless all three are discussed here beginning with Mod
55. fault menu f 90 This note means that the maximum value e g power cp efficiency torgue occurs at one the endpoints over the range of wind speeds specified Thus the maximum is not bracketed by the wind speed range Sometimes this is OK e g a power curve that continues to increase over the range 900 The tip loss effects are modeled somewhat by ignoring the last segment To ignore the last 5 of the blade use 20 segments If you use only 10 segments then the current approach effectively ignores then 10 This brute force approach is crude and it is a little used feature of the code FEA 3k 3k 3K 3K K K K K aK aK ak aK ak aK 3K 3k 3K 3K 3K aa 21 21 21 2K 2K 3K 3K 3K 3K 3K 3K 3K 3K 3K 3K K K aK K K K K K K 2K 3K KK SK SK 3K 3K 3K 3K 3K K K K FEA 3k 3k 3K 3K K ARR I aa Kk 21 21 21 21 KK kk kk 3K K K K Warnings 99 PROPGA code Fitness failed for a particular individual in propga This could be a result of a number of things according to the ierror code TT 3 chord is somewhere a negative number 6 chord is somewhere a negative number 375 The number of angles of attack exceeds that allowed for a PROP93 input file The PROP93 limit is 50 angles of attack 401 The root bending moment at a point off the center of rotation is done by approximately If the offset at which the root bending moment is desired is larger than 10 then a warning is given to indicate that this calculation is an approximation and gets
56. first segment used in analysis last segment used in analysis printout blade element data shaft tilt effects air density slug ft 3 normalized hub cutout normalized hub height blade number cone angle of rotor deg radius ft Normalized chord and twist distribution 51 No stall models used CORRIGAN_EXPN 1 Corrigan inputs are present but not used since stall model is off AIRFOIL MODE 4 4 s814 pd 24 13 3 1 600 6 s814 pd 24 13 3 1 600 6 s812 pd 21 14 33 1 180 6 s813 pd 16 9 3 1 100 6 airfoil family 1 with 4 airfoils r R location and airfoil index AIRFOIL FAMILY 4 0000 1 3000 2 7500 3 1 0000 4 use the first airfoil family the one above USE AIRFOIL FAMILY 1 Enforce tip loss model to always be on TIPON Use the Prandtl tip loss model not the original modified model TIPMODE 2 Design point 64 rpm 2 deg pitch 15 mph DP 1 64 2 15 2 Specify the peak power 500 kW and iterate on the rotor scale NEWT1ISWP 300 500 25501 11999 11999 3 IDES Specify the tip speed 150 mph 220 ft sec and iterate on the rpm at a given design point DP NEWT1IDP 207 220 11 999 121 IDES 52 Determine the rotor power cp and thrust curves 2D SWEEP use pitch setting from design point DP 1 PITCH_DP 1 use rpm from design point DP 1 RPM_DP 1 sweep the wind from 5 to 50 mph in increments of 1 mph WIND_SWEEP 5 50 1 2 perform the sweep 2D SWEEP write out
57. for inspection using the line PRINT INPUT to write the input data to the file tn011 dat RKR GAMMA Line The Weibull shape factor and gamma can be changed using RKR GAMM RKR GAMMA where RKR Weibull shape factor GAMMA gamma Some possible values RKR GAMMA 1 25 0 931840 1 50 0 902745 1 60 0 896574 1 70 0 892244 1 80 0 889287 1 90 0 887363 2 00 0 886227 2 10 0 885694 2 20 0 885625 2 30 0 885915 2 40 0 886482 2 50 0 887264 3 00 0 892979 3 50 0 899747 4 00 0 906402 US standard is RKR 2 29 The defaults is RKR 2 00 and GAMMA 0 886227 RNEWT Line Sometimes it is useful to re initialize the iteration process with the line RNEWT to reset the iteration process anew For example suppose that after a series of NEWT1 and NEWT2 lines the number of variables used for iteration is large RNEWT can be used to reset the iteration so that the next NEWT IDES sequence only iterates on the variables following the RNEWT line In this case the previous specifications will no longer be satisfied 48 RPRINT Line The printing flags can be reset using RPRINT SKIP UNKNOWN WORDS Line To have PROPID skip unknown lines use the on off toggle SKIP UNKNOWN WORDS SUMMARY INFO Line To echo to screen the blade geometric data use SUMMARY INFO The program will report blade radius ft area ft solidity aspect ratio and pitch last used TIPSPEED Line To determine the tipspeed for a given rpm use TIPSPEED
58. fy input variable for iteration see Table CLAMP1 positive step limit used during iteration optional TOL1 optional if CLAMP1 is specified 28 gt 0 and specified gt convergence tolerance for auto iteration mode unspecified gt interactive iteration mode in force It should be noted that in specifying the design point line the wind speed is ignored 999 Also the sweep in wind speed specificied by this line must be in mph Input parameters options for iteration are specified according to Table Table 2 Input Variable Specification for NEWT1 Iteration ITP1 ITP2 ITP3 1 1 Scale Rotor 999 2 Rotor Speed Design Point 3 Pitch Design Point 4 Wind Speed Design Point 5 Cone Angle 999 6 Air Density 999 7 Rotor Radius 999 2 Blade Chord 999 999 100 Offset Chord 3 Blade Twist 999 The in the ITP2 column in Table 2 is used to indicate which segment of the blade is used for iteration Offset Chord means that the blade chord at each segment is increased or decreased by an equal amount which effectively changes the rotor solidity The CLAMP1 sets the step limit for each input variable used for the iteration Some times the predicted change in the input variable is too large and can cause the solution to diverge In this situation specifying a step limit can usually improve convergence If no step limit is desired then the v
59. h 1 xj 1 adjust twist each independently from 9 to 10 with step limit 0 75 newt2 line 2 prescribed cl dist from 2 to 7 relative to 8 at design point rpm 1 pitch 1 xj 1 64 adjust twist each independently from 2 to newti line 5 prescribed a 8 adjust chord uniformly with step limit newt2 line 3 prescribed a dist from 9 to 10 relative to 8 0 020 at design point rpm 1 pitch 1 xj 1 adjust chord each independently from 9 to 10 with step limit newt2 line 4 prescribed a dist from 2 to 7 relative to 8 at design point rpm 1 pitch 1 xj 1 adjust chord each independently from 2 to dry run turned off residues for fnt1 0 1 fnt1_0 2 fnt1 0 3 fnt1_0 4 fnt1_0 5 residues for fnt2_0 fnt2_0 fnt2_0 fnt2_0 fnt2_0 fnt2_0 fnt2_0 fnt2_0 8 fnt2_0 9 fnt2 0 10 fnt2 0 11 fnt2 0 12 1 2 6 7 newt1 equat 00026 00012 02604 00002 00001 0 0 O 0 0 initial wind turbine design for stage ions value1 value1 value1 value1 value1 newt2 equations 3 4 5 fnt2_0 13 fnt2_0 14 fnt2_0 15 fnt2 0 16 00000 00000 00006 00004 00004 00003 00000 00000 00000 00000 00003 00002 00002 00002 00000 00000 value2 value2 value2 value2 value2 value2 value2 value2 value2 value2 value2 value2 value2 value2 value2
60. he following single line e g wtOla in When PROPID runs it will read this file and run this case wt01a in This input file is included the runs directory of the archive Details about how to run PROPID are described in the Shortcourse Notes see Course Materials section and within that see Part II b after reviewing all preceding sections 14 Fil e wtOla in Analysis case Stall Regulated Turbine modeled loosely after the AOC 15 50 Basic input MODE 1 0 INCV 0 0 LTIP 1 0 LHUB 1 0 IBR 1 ISTL 1 0 USEAP WEXP 0 0 NS_NSEC 10 0 1 0 10 0 BE_DATA 1 IS1 IS2 SH 0 RHO 0 0023769 Geometry HUB 0 04 HH 3 333 BN 3 CONE 6 0 RD 24 61 CH_TW 0 O COCCO EC CO oO o 0 0 15 13 12 11 10 09 08 07 06 05 1 0 or N Po 0 0 0 I l N e E HHH HH HHH HH H OF OF HH FF H wind turbine wind turbine mode use tip loss model use hub loss model use brake state model use viterna stall model use swirl suppression boundary layer wind exponent number of blade elements number of sectors first segment used in analysis last segment used in analysis printout blade element data shaft tilt effects air density slug ft 3 normalized hub cutout normalized hub height blade number cone angle of rotor deg radius ft Normalized chord and twist distribution No stall models used CORRIGAN_EXPN 1 Corrigan inputs are present but not used s
61. ince stall model is off AIRFOIL_MODE 4 s814 pd 13 24 1 600 6 15 s814 pd 24 13 3 1 600 6 s812 pd 21 14 33 1 180 6 s813 pd 16 9 3 1 100 6 airfoil family 1 with 4 airfoils r R location and airfoil index AIRFOIL_FAMILY 4 0 0000 1 0 3000 2 0 7500 3 1 0000 4 use the first airfoil family the one above USE_AIRFOIL_FAMILY 1 Enforce tip loss model to always be on TIPON Use the Prandtl tip loss model not the original modified model TIPMODE 2 Design point 64 rpm 2 deg pitch 15 mph DP 1 64 2 15 2 Initiate design does some required preliminary work before analysis IDES Determine the rotor power Cp and thrust curves 2D_SWEEP use pitch setting from design point DP 1 PITCH_DP 1 use rpm from design point DP 1 RPM_DP 1 sweep the wind from 5 to 50 mph in increments of 1 mph WIND SWEEP 5 50 1 2 perform the sweep 2D_SWEEP write out data to files 40 power curve kW vs wind speed mph 45 cp vs TSR 51 rotor thrust lb vs wind speed mph WRITE_FILES 40 45 51 16 Compute the gross annual energy production kwh yr Output the data to file gaep dat Initial avg wind speed 14 mph Final avg wind speed 18 mph Step 2 mph Cutout 45 mph 100 efficiency GAEP 14 18 2 45 15 mph only 85 efficiency GAEP 15 15 1 45 0 85 Obtain aero distributions along the blade 1D_SWEEP PITCH_DP 1 RPM_D
62. ion RADLOC should be set to 0 75 The ZERO TVIST line also properly adjusts the pitch in the DP indexdpODP lines to reflect the true blade pitch with zero twist at the prescribed location 10 Annotated Examples Two examples are provided in this chapter stall regulated turbine and variable speed tur bine Both examples have a design section and an analysis section The input file for each example is given as well as the screen output from running PROPID More examples can be found in the runs directory 50 10 1 Stall Regulated The first example is of a stall regulated turbine The example is based on the wt06a run case In this example the peak power and tip speed have been specified The rotor scale is iterated to achieve the peak power and the rpm is iterated to achieve the tip speed File wt06a in Stall Regulated Turbine Basic input MODE 1 0 INCV 0 0 LTIP 1 0 LHUB 1 0 IBR 1 0 ISTL 1 0 USEAP 1 WEXP 0 0 NS NSEC 10 0 IS1 1 0 IS2 10 0 BE DATA 1 SH 0 0 RHO 0 0023769 Geometry HUB 0 04 HH 3 333 BN 3 CONE 6 0 RD 24 61 CH_TW 0 15 13 12 11 10 09 08 07 06 05 O OCS E CEC C Oo 1 0 O H ND 6PF6O O 0 O I I N e E H H FR H HH HOH H HOF OF H H H FR wind turbine wind turbine mode use tip loss model use hub loss model use brake state model use viterna stall model use swirl suppression boundary layer wind exponent number of blade elements number of sectors
63. itch A Pitch Wind Speed A Wind Speed TSR Cone Angle A Cone Angle Air Density A Air Density Rotor Radius A Rotor Radius 2 Blade Chord A Nondimensional Blade Chord 0 05 Offset Chord A Nondimensional Offset Chord 0 05 Blade Twist A Blade Twist 2 All Chords A Chord 0 05 All Twists A Twist 2 5 NEWT1 case 5 NEWT2 case no suggested value rarely used 9 Additional Input Lines ATOL Line The convergence parameter for the PROP portion of the code can be set with ATOL ATOL This line is optional and if it is not used the default value is 0 000001 42 BE DATA Line Blade element performance data like that of the PROPSH code can be written to ftn011 dat with the line BE DATA IS where if IS is 1 data is saved to file default 0 no data saved If data is printed in the design mode the file can become thousands of lines long Also during the design mode the data is not particularly useful since the blade geometry and other parameters may be changing The BE DATA line is most useful during the analysis performed after the design process When this data is desired during the analysis mode the BE DATA line should precede the 2D SWEEP and 1D SWEEP lines BEEP Line Beeps to the screen can be sent with the line BEEP This feature is not supported on all platforms BUMPCL BUMPCD and BUMPALPHA Lines To explore what if
64. ivities for newtl design parameter 2 residues for newti equations fnti_1 1 3 90724 valuei 496 09276 deltasi 0 01068 clamp1 0 300 fnti_1 2 0 28724 valuei 219 71276 deltasi 1 09330 iteration 5 calculating sensitivities for newtl design parameter 1 calculating sensitivities for newtl design parameter 2 59 residues for newti equations fnt1 1 1 0 09755 valuei 500 09755 deltasi 0 00191 clamp1 0 300 fnt1 1 2 0 00614 valuei 220 00614 deltasi 0 03003 iteration 6 calculating sensitivities for newtl design parameter 1 calculating sensitivities for newtl design parameter 2 residues for newti equations fnt11 1 0 00094 valuei 499 99906 deltasi 0 00005 clamp1 0 300 fnti_1 2 0 00002 valuei 219 99998 deltasi 0 00134 select option 0 stop iteration for current stage number of consecutive iterations 999 to stop execution 99 more options gt gt 1 iteration 7 calculating sensitivities for newtl design parameter 1 calculating sensitivities for newtl design parameter 2 residues for newti equations fnti 1 1 0 00002 valuei 499 99998 deltasi 0 00000 clamp1 0 300 fnt1 1 2 0 00000 valuei 220 00000 deltasi 0 00004 select option 0 stop iteration for current stage number of consecutive iterations 999 to stop execution 99 more options gt gt 0 Performing 2D sweep analysis gt Done performing
65. lative chord and twist distributions must start with a radius of O and end at 1 9319 DU_MODEL line must come before the AIRFOIL_MODE line because right after the AIRFOIL_MODE line the data is modified according to the preceeding Du line 81 9320 CORRIGAN EXPN line must come before the AIRFOIL MODE line because right after the AIRFOIL MODE line the data is modified according to the preceeding Corrigan line 9321 It is suspected that the start and end angles on the Du model were not included in the airfoil mode line input data Including the DU MODEL line requires the start and end angles 9322 It is suspected that the clmax and insert angle for the Corrigan model were not included in the airfoil mode line input data Including the CORRIGAN EXPN line requires this data 9390 PROPID reguires that the drag data extend to 27 5 deg 9404 There are too many points in the 2D sweep line Currently ncl is 25 Reduce the number of values sweeps in pitch tsr or rpm The number of wind speed points does not have to be reduced See PROPID history file 980806 for more details 9405 Similar to 9404 Currently nbl is 20 1 Jan 2010 9406 You cannot use a WIND_FIXED line w the 2D_SWEEP line If you want just one wind speed then you can use the WIND_SWEEP line with say 10 10 1 2 so that only 10 mph is considered 9801 When using the CHORD_RELATIVE line the first and last values in radius should be 0 and 1 respectively So the d
66. meter parameter parameter parameter parameter parameter parameter parameter parameter parameter parameter N O 0 P OWN 0 BP W N KE calculating sensitivities for newt2 design parameter 8 calculating sensitivities for newt2 design parameter 9 calculating sensitivities for newt2 design parameter 10 calculating sensitivities for newt2 design parameter 11 calculating sensitivities for newt2 design parameter 12 calculating sensitivities for newt2 design parameter 13 calculating sensitivities for newt2 design parameter 14 calculating sensitivities for newt2 design parameter 15 calculating sensitivities for newt2 design parameter 16 residues for newti equations fnt1_1 1 0 00000 valuei 140 80000 deltasi 0 00002 fnt1_1 2 0 00000 valuei 264 00000 deltasi 0 00005 fnt1_1 3 0 00244 value1 1000 00244 deltasi 0 00011 fnt1_1 4 0 00000 value1 1 00000 deltasi 0 00001 clamp1 0 750 fnt1_1 5 0 00000 value1 0 33300 deltasi 0 00000 clamp1 0 020 residues for newt2 equations fnt2_1 1 0 00000 value2 0 95000 deltas2 0 00001 clamp2 0 750 fnt2_1 2 0 00000 value2 0 90000 deltas2 0 00002 clamp2 0 750 fnt2_1 3 0 00001 value2 1 30001 deltas2 0 00003 clamp2 0 750 fnt2_1 4 0 00000 value2 1 25000 deltas2 0 00001 clamp2 0 750 fnt2_1 5 0 00000 value2 1 20000 deltas2 0 00002 clamp2 0 750 fnt2_1 6
67. n fact the speed corresponding to the desired C cannot be specified rather this speed must be determined since it is predefined somewhat by the cut in and peak power speeds This wind speed shown in Fig 4 see point 2 is determined by the additional lines NEWT1LDP 500 8 0 65 112 142 1 IDES which in the input file follows the previous lines for the peak power prescription As indicated by this line the C is specified to be 0 65 at segment 8 75 of radius for a rotor speed of 50 rpm and blade pitch of 2 5 deg The wind speed for the second design point is adjusted to achieve the desired lift coefficient on segment 8 The IDES line begins the second iteration stage for both the design point wind speed as well as the blade chord offset so that the desired peak power and local lift coefficient are achieved Thus a two dimensional iteration is performed N In the next stage the twist 0 is adjusted to achieve the desired Cy as shown in Fig 5 see solid line In particular the twist inboard of 75 radius is adjusted to achieve the desired inboard C Also the outboard twist is iterated to achieve the desired outboard Ci In general the NEWT2SDDP line is used to adjust either the relative chord or twist dis tribution to achieve a desired relative output distribution The NEWT2SDDP line is given 36 Specified Lift Coefficient Distribution CI 0 00 0 25 0 50 0 75 1 00 r Figure 3 Desired C distribution corresponding to a wi
68. nd speed yet to be determined by NEWT2SDDP IFTP2 JSEGIX2 JSEGIX3 JSEGREL KADJSBS sss D ssF 1 SSS KADJSBS SSF KADJSBS KDPRPM2 KDPFL2 KDPXJ2 ISDTP ISCHED2 CLAMP2 TOL2 where IFTP1 100 gt relative lift coefficient distribution 101 gt relative axial induction factor distribution 102 gt relative airfoil angle of attack distribution 104 gt relative power coefficient distribution 105 gt relative power distribution JSEGIX2 inboard segment for relative distribution JSEGIX3 outboard segment for relative distribution JSEGREL relative segment i e where the relative distribution is 0 KADJSBS number of segments JSEGIX3 JSEGIX2 SSS 1 first segment prescribed always 1 SSF 1 relative value for first segment SSS KADJSBS last segment prescribed always JSEGREL SSF KADJSBS relative value for last segment KDPRPM2 design point for rotor speed KDPFL2 design point for blade pitch KDPXJ2 design point for wind speed ISDTP used to identify input variable for iteration see Table 37 Rotor Power kV CI 00 te iih 0 00 0 25 0 50 0 75 1 00 r Figure 4 Adjustment of wind speed to achieve desired C at 75 radius ISCHED2 used to identify input variable for iteration see Table CLAMP2 positive step limit used during iteration opti
69. ng comments Arrays and elements of arrays are denoted for example by CH and CH 1 or CH JSEG respectively JSEG is used to denote the jth element of the blade ISEG is the total number of blade elements Finally a character in this user manual denotes the continuation of an input line The however is not used in the actual input data file Some rules apply to the sequence of lines First required input data Chapter B must precede lines that initiate design and analysis These lines can be in any order Second some lines initiate the input of a seguence of data e g the AIRFOIL MODE line Section 3 3 Comments are sometimes used in this manual to indicate the beginning and ending of a seguence of data 3 Reguired Data for Design and Analysis Modes The following lines are used to input data that is reguired for design and analysis Only brief descriptions are given since further details can be found in Ref 6 which is included in the PROPID distribution archive 3 1 Basic Setup Parameters The following lines are used to set single parameters and options MODE MODE INCV INCV LTIP LTIP LHUB LHUB IBR IBR SH SH ISTL ISTL USEAP USEAP WEXP WEXP RHO RHO RD RD HUB HUB HH HH CONE CONE BN BN NS NSEC NS IS1 IS1 Is2 182 where MODE 1 gt 2 gt INCV 0 gt 1 gt LTIP 0 gt 1 gt LHUB 0 gt 1 gt IBR 0 gt 1 gt SH 0 gt 1 gt ISTL
70. nted in Chapter 4 Once the operating conditions are specified as well as the various input parameters some of which may change through iteration an analysis of the rotor can be performed as discussed in Chapter 5 Several example input files are included in the runs directory of the archive This manual discusses an example input file loosely modeled on the AOC 15 50 stall regulated wind turbine It is presented in Chapter 6 Chapter 7 discusses how output files e g power curve blade chord distribution etc are generated The design mode is discussed in Chapter Bland many additional input lines are briefly discussed in Chapter 9 In Chapter IO an annotated input file is presented All attempts are made to ensure that old PROPID files will run with newer versions of the code More on PROPID can be found on the UIUC Applied Aerodynamics Group web page http www ae illinois edu m selig 2 Reading this User Manual PROPID is a keyword based code The input file see Chapter 6 is a script type file that contains a journal of commands for either batch mode execution or interactive use Three basic data line types are used in the input file as follows Example lines MODE 1 This line is commented out and will be ignored This line is also commented out The line MODE 1 is a line type that prompts action either that of storing data for future calculations or initiating either design or analysis calculations Lines that d
71. o not start in the first column are ignored If a keyword is not recognized then the line will be echoed to the screen and user will be given the option of proceeding or stopping Note that the values following the line are read in unformatted mode however values beyond column 82 will not be read The or character in the first column denotes that the line is to be ignored Most data lines can have trailing comments like this example below Example LTIP 1 use Prandtl tip loss model Lines that cannot have trailing comments are those with optional data on the line as discussed later The character in the last line is the stop line which denotes the end of the input and stops execution Anything following the stop line is ignored In the following descriptions of the lines this format will be used MODE MODE The string MODE denotes that the value following the line name will be set to the program variable MODE For instance a 1 for MODE indicates that MODE 1 In some cases all of the values on a line will not be used in which case 999 will be used as a dummy value Dots indicate that there are one or several intervening lines A character that separates a string of input parameters e g P1 P2 P3 means that the values past the need not be entered if the defaults are acceptable The actual input file does not contain the character As previously mentioned lines with optional data cannot have traili
72. oads are then calculated using the following line CALC LOADS IMODE IOUT where IMODE 1 gt Calculate the hurricane loads based on the HURRICANE SPECS line 2 gt Set the load based on the last prop f run IOUT 1 gt Write output to screen 46 ITERMAX Line When tolerances are specified for the automatic convergence mode the maximum number of iterations can be specified with ITERMAX ITERMAX where ITERMAX is the maximum number of iterations Iteration will then be performed until either convergence is reached or the number of iterations exceeds the maximum speci fied ITERPROP Line The maximum number of iterations used for BEMT convergence can be set by ITERPROP ITERPROP where ITERPROP is the maximum number of iterations This is used in prop f LCOL45 Line When in VS MODE to optionally have Cp TSR output to file 45 ftn045 dat use the toggle line LCOL45 Note that in the example that follows the input file must also include the VS MODE line ahead of this point Example LCOL45 PITCH_DP 1 TSR_SWEEP 4 15 5 WIND_SWEEP 16 16 1 2 2D_SWEEP WRITE_FILES 45 Applying the line LCOL45 again will toggle the function off PAUSE Line To pause program execution the input file should contain the line PAUSE Program execution will then continue when a return is entered interactively 47 PRINT INPUT Line As with the original PROPSH code the input data can be written out
73. oil and the insert angle ALINSERT for the model are read If only the UIUC model is used the Corrigan CLMAXN and ALINSERT are still needed as place holders Finally if the Corrigan model is used the line CORRIGAN_EXPN is required and must appear before the AIRFOIL_MODE group of lines The format is given by CORRIGAN_EXPN EXPN where the recommended value for the empirical constant EXPN is 1 see Ref 8 The last mode is 3 and it differs from mode 4 in only one respect The order of the airfoil data in the pd files must be Cy Cg a When using AIRFOIL MODE 3 and 4 PROPID uses that information to read in airfoil data tables After this point the distribution of airfoils to be used along the blade needs to be defined using the AIRFOIL FAMILY lines AIRFOIL FAMILY KNODE IAFMLY AFX IAFMLY 1 LIDXAF IAFMLY JNODE BLENDDST IAFMLY JNODE AFX IAFMLY JNODE J LIDXAF IAFMLY JNODE BLENDDST IAFMLY JNODE AFX IAFMLY KNODE IAFMLY IDXAF IAFMLY KNODE IAFMLY BLENDDST IAFMLY KNODE JNODE J where KNODE defines the number airfoils to be used in the airfoil family AFX radial location of airfoil IDXAF IDXAF the index of the airfoil listed in the AIRFOIL MODE line BLENDDST the distribution function used to determine blending The optional BLENDDST defines the blending distribution function used with determining the airfoil coefficients The first BLENDDST must be 1 and the last v
74. onal TOL2 optional if CLAMP2 is specified gt 0 and specified gt convergence tolerance for auto iteration mode unspecified gt interactive iteration mode in force The input parameter options for iteration are specified according to the Table B The blade twist adjustment shown in Fig 5 is performed according to the example lines NEWT2SDDP 100 2 7 8 6 1 0 308 2 0 302 3 0 276 4 0 218 38 Twist deg 0 00 0 25 0 50 0 75 1 00 CI 0 5 0 0 0 00 0 25 0 50 0 75 1 00 r Figure 5 Adjustment of twist distribution to achieve desired O distribution 5 0 118 6 0 042 112 2 100 2 NEWT2SDDP 100 9 10 8 2 1 030 2 053 112 2 100 2 IDES The first NEWT2SDDP line prescribes the C from segments 2 through 7 relative to 8 Six values for C then follow At segment 2 the C is prescribed to be 0 308 0 302 for segment 3 and so on The specification corresponds to a rotor speed of 50 rpm and pitch of 2 5 deg The wind speed corresponds to that of the second design point which is changing according to the previous NEWT1LDP line To achieve the desired C1 the corresponding twist is adjusted for segments 2 through 7 The second NEWT2SDDP line prescribes the C from segments 9 through 10 relative to 8 Again the twist is adjusted for the corresponding segments 9 and 10 Note that for this example the twist for segment 8 is left unchanged at 0 deg Therefore 39 Table 3 Input Variable Specification for
75. oo close to C For instance if C7 is 1 2 and the specified local lift coefficient is 1 1 two different solutions exist one before stall and one after The user may assume that the specified C will be achieved at an angle of attack below Crna however it could also be achieved for an angle of attack above Cimas The wind turbine must be analyzed to determine which case exists after iteration To avoid this potential difficulty it is suggested that the specified C be at least 0 2 below C7 Hub radius cut out No specifications should be applied to those segments that are within the hub radius or cut out or those segments that are not included in the analysis by the IS1 and IS2 lines Errors and Warnings There are several checks in the code for errors and potential errors For instance if the peak power is specified for a rotor and iteration is performed on the blade chord offset the local chord can become negative at which point an error will be issued to the user It is easy to envision a case for which this could occur If the actually peak power is greater than the prescribed peak power the chord will be reduced everywhere by an egual amount The iteration process will be repeated as long as the actually peak power is greater than the prescribed peak power At some point the local chord could be reduce to a negative value most likely at the tip Since the data is always checked between iterations an error to this
76. or power then a NEWT1 type line is used If a function is prescribed e g lift coefficient distribution then a NEWT2 type line is used Any number of NEWT1 and NEWT2 type lines can be used as long as no two lines specify the same desired output or input for adjustment If no solution is found it usually indicates that either 1 the above rule is violated by mistake or 2 the desired output is not physically possible 8 1 NEWT1 Lines The NEWT1ISWP can be used to specify a desired peak power or some other variable that is determined by analyzing the rotor over a given wind speed range The general form of the NEWT1ISWP line is given by NEWT1ISWP IFTP1 FNEWT1 XJSNT1 XJFNT1 DXJNT1 KDPRPM1 KDPFL1 KDPXJ1 ITP1 ITP2 ITP3 1 CLAMP1 TOL1 where IFTP1 300 gt peak rotor power kW 301 gt wind speed mph at peak power 302 gt peak power coefficient 304 gt maximum torque ft 1b FNEWT1 value for specified parameter XJSNT1 lowest value for wind speed mph for range XJFNT1 highest value for wind speed mph for range DXJNT1 increment in wind speed mph KDPRPM1 design point for rotor speed KDPFL1 design point for blade pitch KDPXJ1 999 value is ignored ITP1 used to identify input variable for iteration see Table ITP2 used to identify input variable for iteration see Table ITP3 used to identi
77. ove analyze a rotor using the PITCH and RPM from the first design point A 1D sweep is performed from 5 to 30 mph in 5 mph increments and the C and chord in feet are written to their respective files The results for this example was taken from the wt01a run case The output written to each file follows ftn085 dat 0 050 0 4456 1 0842 1 5284 1 0512 0 9517 0 8822 0 150 0 2513 0 8460 1 4827 1 1229 1 0110 0 9339 0 250 0 1458 0 5703 1 1158 1 6000 1 2035 1 0952 0 350 0 0989 0 4223 0 8754 1 3826 1 5209 1 2329 0 450 0 0948 0 3805 0 7789 1 2306 1 4563 1 2951 0 550 0 1101 0 3782 0 7406 1 1560 1 3545 1 3120 0 650 0 1181 0 2465 0 7055 1 0902 1 2426 1 2685 0 750 0 1355 0 3771 0 6953 1 0465 1 1351 1 1762 0 850 0 1798 0 4175 0 7159 1 0168 1 1145 1 1315 0 950 0 2421 0 4730 0 7074 0 9402 1 1043 1 1057 ftn095 dat 1 2305 3 69150 3 6915 3 19930 6 1525 2 95320 8 6135 2 70710 11 0745 2 46100 13 5355 2 21490 15 9965 1 96880 18 4575 1 72270 20 9185 1 47660 23 3795 1 23050 24 6100 1 10745 7 3 Reporting Lines Different parameters can be written to a report file and written to the screen All of the REPORT lines listed in this section will write data to screen If the data is to be also written to an output file the following two lines need to be included REPORT_START open the file for reporting REPORT_END close the file for reporting 22 Any REPORT lines between the REPORT START and REPORT END lines will be written to the file ftn082 dat The ou
78. p2 0 750 fnt2_1 7 0 00000 value2 1 10000 deltas2 0 00001 clamp2 0 750 fnt2 1 8 0 00000 value2 1 05000 deltas2 0 00002 clamp2 0 750 fnt2_1 9 0 00000 value2 0 33300 deltas2 0 00000 clamp2 0 020 fnt2_1 10 0 00000 value2 0 33300 deltas2 0 00000 clamp2 0 020 fnt2_1 11 0 00000 value2 0 33300 deltas2 0 00000 clamp2 0 020 fnt2 1 12 0 00000 value2 0 33300 deltas2 0 00000 clamp2 0 020 fnt2 1 13 0 00000 value2 0 33300 deltas2 0 00000 clamp2 0 020 fnt2_1 14 0 00000 value2 0 33300 deltas2 0 00000 clamp2 0 020 fnt2_1 15 0 00000 value2 0 33300 deltas2 0 00000 clamp2 0 020 fnt2_1 16 0 00000 value2 0 33300 deltas2 0 00000 clamp2 0 020 select option 0 stop iteration for current stage number of consecutive iterations 999 to stop execution 99 more options gt gt 0 Note 10 running in variable speed const tsr mode Performing 2D sweep analysis gt Done performing 2D sweep analysis OCA CAA EKK k kkk k kkk KK KK x Output 70 average wind speed mph cutout wind speed mph rotor cp vs v gt ftn045 dat OAR kk kkk kk kkk kk I A A kk kk kk k Performing 2D sweep analysis gt Done performing 2D sweep analysis KKK K K FK FK 3 K K K K K K FK FK FK K K K K K 2K K FK FK FK FK K K K K K FK FK FK FK K K K K K K IK K K rotor p vs v gt ftn040 dat rotor thrust vs wind spe
79. pid in gt wt09b man in OO kkk kkk k kkk kkk IC A A I kk kk kk k k k The gt gt are user supplied input during the PROPID execution References 1 Selig M S and Tangler J L A Multipoint Inverse Design Method for Horizontal Axis Wind Turbines presented at the AWEA WINDPOWER 94 Conference Minneapolis Minnesota May 9 12 1994 2 Selig M S and Maughmer M D Multipoint Inverse Airfoil Design Method Based on Conformal Mapping AIAA Journal Vol 30 No 5 May 1992 pp 1162 1170 3 Selig M S Multipoint Inverse Design of an Infinite Cascade of Airfoils AIAA Journal Vol 32 No 4 1994 pp 774 782 4 Tangler J Smith B Kelley N and Jager D Measured and Predicted Rotor Perfor mance for the SERI Advanced Wind Turbine Blades NREL TP 257 4594 Feb 1992 5 Hibbs B and Radkey R L Small Wind Energy Conversion Systems SWECS Ro tor Performance Model Comparison Study Aerovironment Inc prepared for Rockwell International Corporation Nov 1981 6 Tangler J L A Horizontal Axis Wind Turbine Performance Prediction Code for Per sonal Computers User s Guide Solar Energy Research Institure Jan 1987 7 Corrigan J J and Schilling J J Empirical Model for Stall Delay Due to Rotation American Helicopter Society Aeromechanics Specialists Conf San Francisco CA Jan 1994 8 Tangler J L and Selig M S An Evaluation of an Empirical
80. ported using the REPORT SPECIAL line This report line has three flags as seen below that are explained in Table The JPT value for IRSTP3 is with 25 report values that are created with a 1D SWEEP and is used to specify which sweep result should be reported A value of 1 provides the radial position a 2 provides the first sweep result a 3 provides the second sweep results and so on REPORT SPECIAL IRSTP1 IRSTP2 IRSTP3 Table 1 Flag Values for REPORT SPECIAL IRSTP1 IRSTP2 IRSTP3 Description 1 1 999 FIXV speed corresponding to that for which the power is truncated via the FIXPD line 2 1 2 3 ISEG JPT blade section cl cd at blade station IRSTP2 3 999 999 root bending moment lb ft from last analysis 4 1 2 3 ISEG JPT blade physical thickness in at blade station IRSTP2 5 1 2 3 ISEG JPT blade twist deg at blade station IRSPT2 6 999 999 air density slugs ft 7 999 999 tip speed ratio based on last analysis run 8 999 999 annual energy production and corresponding average wind speed and generator efficiency 9 999 999 write airfoil data file names used 10 1 2 3 ISEG JPT blade chord ft at blade station IRSPT2 11 999 999 FIXPD 12 1 2 3 ISEG JPT blade section Re at blade station IRSPT2 15 1 2 3 ISEG JPT blade section axial induction factor at blade station IRSPT2 14 1 2 3 ISEG JPT blade section lift coefficient at blade station I
81. r newt2 design parameter 5 calculating sensitivities for newt2 design parameter 6 calculating sensitivities for newt2 design parameter 7 calculating sensitivities for newt2 design parameter 8 calculating sensitivities for newt2 design parameter 9 calculating sensitivities for newt2 design parameter 10 calculating sensitivities for newt2 design parameter 11 calculating sensitivities for newt2 design parameter 12 calculating sensitivities for newt2 design parameter 13 calculating sensitivities for newt2 design parameter 14 calculating sensitivities for newt2 design parameter 15 calculating sensitivities for newt2 design parameter 16 residues for newti equations fnt1_1 1 0 00000 valuei 140 80000 deltas1 fnt1_1 2 0 00000 value1 264 00000 deltas1 fnt1_1 3 0 00017 valuei 999 99983 deltasi fnt1 1 4 0 00000 value1i 1 00000 deltasi clamp1 0 750 fnti 1 5 0 00000 valuel 0 33300 deltasi clamp1 0 020 residues for newt2 eguations fnt2 1 1 0 00000 value2 0 95000 deltas2 clamp2 0 750 fnt2 1 2 0 00000 value2 0 90000 deltas2 0 00001 clamp2 0 750 fnt2_1 3 0 00001 value2 1 29999 deltas2 0 00003 clamp2 0 750 fnt2 1 4 0 00000 value2 1 25000 deltas2 0 00003 clamp2 0 750 fnt2 1 5 0 00000 value2 1 20000 deltas2 0 00001 clamp2 0 750 fnt2 1 6 0 00000 value2 1 15000 deltas2 0 00001 clam
82. radial loc Cl no spec for this segment 15 30 25 25 35 20 45 15 55 10 65 05 75 00 85 95 95 90 SE HH H H R R H H H R OF O 0 NJ O 0 2 U N O COCO O CO O O oO oO O OH HH H H H be oO Stage 1 Iterate on the RPM DP1 to get a tip speed of Specify a tip speed TSR wind speed to be consistent with the design tip speed ratio of 6 and the given wind speed DP1 For the first design point with a wind speed of 16 mph tip speed is 6 16 88 60 140 8 NEWT1IDP 207 140 8 1 999 1 121 IDES Stage 2 Do the same thing for the second design point iterating on its RPM to yield a TSR of 6 60 For DP2 the wind speed is 30 mph Hence the tip speed is 6 x 30 88 60 264 NEWT1IDP 207 264 2 999 2 122 IDES Write out the results REPORT START REPORT DP 1 1 1 REPORT 1IDP 207 1 999 1 REPORT 1IDP 208 1 999 1 REPORT SEPARATOR REPORT DP 2 2 2 REPORT 1IDP 207 2 999 2 REPORT_1IDP 208 1 999 1 Stage 3 Specify the rated power to be 1000 kW 1MW at 30 mph DP2 Remember to also update the FIXPD line below to crop the power curve at this set level 1 MW NEWT1IDP 200 1000 212 1 1 999 IDES Stage 4 Iterate on pitch to get cl r R 75 1 00 NEWT1LDP 500 8 1 00 111 131 75 IDES Stage 5 Iterate on twist to get cl 9 10 NEWT2SDDP 100 9108 2 1 05 2 5 10 111 2 100 75 IDES Stage 6 Iterate on twist to get cl 2 7
83. red sequentially as they are defined by each successive AIRFOIL_FAMILY line To define which airfoil family to used in the blade analysis the USE_AIRFOIL_FAMILY KAFMLY where KAFMLY the index of the airfoil family to use Example define airfoils using mode 4 alpha cl cd AIRFOIL_MODE 4 3 s818smoo_e pd 0 24 12 O 1 65 o 0 0 s816smoo_e pd 0 21 10 O 1 25 0 0 0 s817smoo_e pd 0 16 8 0 1 10 o 0 0 airfoil family 1 with 3 airfoils r R location and airfoil index AIRFOIL_FAMILY 3 0 00 1 0 50 2 1 00 3 use the first airfoil family the one above USE_AIRFOIL_FAMILY 1 In the above example three airfoils are used to determine the blade geometry and aero dynamics Since no airfoil blending distribution was defined in the AIRFOIL FAMILY lines the airfoil data will be linearly interpolated between the airfoil locations It should be noted that airfoil data is linearly interpolated with respect to the angle of attack and the Reynolds number 11 4 Design Points for Design and Analysis Modes For both design and analysis modes the DP line can be used to enter the conditions for which the wind turbine is to be analyzed These conditions are entered using DP IDP RPMDPCIDP FLDP IDP XJDP IDP IXDIMDP IDP where IDP design point number must be unique RPMDP IDP rotor speed rpm FLDP IDP blade pitch deg at 75 of radius XJDP IDP speed as indicated by the units parameter IXDIMDP IDP IXD
84. t from the value at point B The flat plate model starts at point C and the lift curve proceeds to point D and beyond The location of point C on B E will depend on the magnitude of the stall delay angle This is explained in Figure 7 This approach to defining the airfoil Cj a curve is best when airfoil data up to stall is available and the airfoil is known to have a gentle stall and data after stall is not available The history behind having a variable stall delay angle B C traces to when a stall delay angle was used to model the stall delay effect of constant speed stall regulated wind turbines This stall delay effect is largest over the inboard part of the blade and is reduced to a neglible amount outboard In other words the delay stall inboard can be modeled by using a higher stall delay inboard than outboard which should behave in a 2D manner with no stall delay other than that of the 2D performance By varying the stall delay angle the importance of blade rotation effects that cause stall delay can be examined Figure 7 shows the effect of increasing the stall delay angle A larger stall delay angle moves point C to C as shown in the figure The flat plate model will start at point C Points A B C D will now describe the lift curve Figure 8 shows that PROPID does not use any of the input data after the stall angle As shown the code takes the C value at the stall angle B and holds that value until stall 73 G O St
85. tal stall data from clmax and beyond D a Flat plate model Stall Stan stalidelay Figure 10 The UIUC post stall model shown and Corrigan model not shown 76 Appendix B Warnings and Errors DR 2 KK K K FK FK K K K K K K FK FK FK FK a KK K K 2K aj KK KK ak K a K akk FK FK aj FK K akk K a K KK akk akk KK FK akk akk ae FK FK FK FK FK ae KK K K KK KK KK KK K K OK Key Notes Messages to inform the user Warnings Information that the user should understand Usually a warning is harmless Errors Program failure Something is seriously wrong and the code is about to crash or simply give bad data It is usually a sign of an error in the user input data kk ak ak ak aK 3k 3k 3K 3K K ARR IR I I I I I K KK KK 3K 3K kk 3K K K K kk k ak AA K K K aK aK 2K 2K 2K aK 3k 3k I I I I I KK SK SK kk kk kk K K Caveat Some comments in these notes warnings and error messages are informational useful only to the developers So if something is not clear it might fall in this developer category FEA 3k 3K 3K 3K K K K K aK aK aK ak ak ak CCCI I A I A I K K 1 21 21 21 21 21 21 21 25 1 1 3K 3K 3K 3K 3K 3K 3K K K AC aK aK AR A akk KK kk kk 3K K K K SRI 2K 2K 2K K K 2K 2K 2K FK 2K K K K K 2K FK FK 2K K K K K FK a FK 2K 2K K K K FK FK aK 2 K K 2k KKK KKK K K Notes 10 This comment is relevant only when lrpmfix is used which for now is only in prpswp2 f for writing out fort 45 In deflt f lrpmfix tt by de
86. tput for each REPORT line is followed by a number as shown in the following example This number is a counter that keeps track of the number of output lines from any REPORT line These numbers are provided for both the output to the screen and the optional output file ftn082 dat Example REPORT_START REPORT_COMMENT This is a comment REPORT_GEOMETRY 1 REPORT_SEPARATOR REPORT_DP_LAST REPORT_END The output would look similar to following KAKKKKKKKKKKKK Reporting On Heed 1 This is a comment Midi Ja ae 2 blade radius ft 24 610 3 r JB ES AL CHEE EE PAE DDS SS stn topi DE SOS 4 last used design point 5 blade rpm 64 000 6 blade pitch deg 2 000 7 blade xj 30 000 8 blade tsr 3 749 9 KAKKKKKKKKKKKK Reporting Off eee 10 As seen in the above example a comment can be added to the output by using REPORT COMMENT Only the first 50 characters after the REPORT COMMENT will be written A line of dashes can be added as a separator by using REPORT SEPARATOR Also the blade geometry is written when the following line is used REPORT GEOMETRY IRGTP Where IRGTP gt radius ft gt area per blade ft 2 solidity gt aspect ratio ll PP O N l v 23 The solidity is the total blade area divided by the disc area area per blade x number of blades lidity Ha t x radius The aspect ratio is the radius squared divided by the area of one blade radius
87. tt gt airfoil Re gt Re of data somewhere endprog f BOCA aa kkk kkk KK ak KK kkk kk PROPID Successful run x Closing input file propid in gt wt06a in ORO aa k aa a aak ak ak KK kkk k k k k The gt gt are user supplied input during the PROPID execution 10 2 Variable Speed This example is for a variable speed turbine The input file is based on the wt09b run case In this example the rpm is iterated to achieve a tip speed ratio of 6 The rotor is scaled to achieve a rated power of 1 MW and the pitch and twist are iterated to achieve a desired lift coefficient distribution Finally the chord is iterated to achieve an axial induction factor of 0 333 Some report lines are also included in this case The input file is essentially converged but a few iterations will still be performed File wt09b in Variable Speed Turbine Debugging Feature Echo the input lines to the screen The error can be isolated to one line HECHO INPUT This file includes converged data from wt09a in Basic input MODE 1 0 wind turbine INCV 0 0 wind turbine mode LTIP 1 0 use tip loss model LHUB 1 0 use hub loss model IBR 1 0 use brake state model ISTL 1 0 use viterna stall model USEAP 1 0 use swirl suppression WEXP 0 0 boundary layer wind exponent NS_NSEC 10 0 1 0 number of blade elements number of sectors Ist 1 0 first segment used in analysis IS2 10 0 last segment used in analysis
88. uations 01466 valuei 02749 valuei 36556 valuei 00010 valuei fnt1 1 5 00006 value1i residues for newt2 fnt2_1 1 0 eguations 00001 value2 66 design design design design design design design design design design design design design design design design design design design design design 140 78534 263 97251 999 63444 1 00010 0 33294 parameter parameter parameter parameter parameter parameter parameter parameter parameter parameter parameter parameter parameter parameter parameter parameter parameter parameter parameter parameter parameter O 0 J O 0 P UD 0 EP O N KE Ho f H o p O 01 P W N O deltas1 deltas1 deltas1 deltas1 0 00004 0 00001 0 00000 0 00041 clamp1 0 750 deltasi 0 00000 clamp1 0 020 0 95009 deltas2 0 00004 fnt2 1 fnt2 1 fnt2 1 fnt2 1 fnt2 1 fnt2 1 fnt2_1 fnt2_1 fnt2 1 1 fnt2 1 1 fnt2 1 1 fnt2 1 1 fnt2 1 1 fnt2 1 1 fnt2 1 1 iteration calculating calculating calculating calculating calculating calculating calculating calculating calculating calculating calculating calculating 2 0 00000 3 0 00049 4 0 00029 5 0 00022 6 0 00018 7 0 00004 8 0 00002 9 0 00001 0 0 00003 1 0 00023 2 0 00015 3 0 00013 4 0 00011 5 0 00002 6 0 00001 2 sensitivities sensitivities sensitivities
89. worse with increasing offset roffset in the REPORT MD ROFFSET line 433 When debugging w lui7 and 1u18 dct and a2 in prop f you need to use the CATA line before any prop runs This will reset the cata1 and cata2 arrays before doing a prop run and storing the dct and a2 convergence history for a particular wind speed 450 The lowest Reynolds number for which airfoil data is available pd file is higher than that found during the prop performance analysis prop f In this case the code will force the Reynolds number during the run to be the lowest value found in the pd file What this means is that the analysis is likely to overpredict the performance since the higher degradation w the actual lower Re is not accounted for in the analysis Usually this overprediction is very small unless it occurs during the stalled state in which case the correct Cl is important 451 Same as 450 above but this time the Re is above the Re in the pd file 500 Some undocumented generator functions GENFUN line require the rpm Be sure that you write this file using the WRITE_FILES line if you need to know the rpm to obtain the generator efficiency menu f 850 Warning with airfoil mode 2 airfoil model This feature is currently unsupported 855 This line MAKE_PROP_AFDATA works w all stall delay models except the RAJ_MODEL This code was written by Nikil Raj but his thesis model RAJ_MODEL line was not implemented see
90. ws The first allows for the specification of integrated quantities e g power for a given design point IDP NEWT1IDP IFTP1 FNEWT1 KDPRPM1 KDPFL1 KDPXJ1 ITP1 ITP2 ITP3 CLAMP1 TOL1 where IFTP1 200 gt power kW 202 gt Thrust lb 203 gt Moment lb ft 205 gt Power coef 33 206 gt Torgue ft 1b 207 gt Tip Speed ft sec FNEWT1 value for specified parameter KDPRPM1 design point for rotor speed KDPFL1 design point for blade pitch KDPXJ1 design point for wind speed The parameters ITP1 etc are the same as previously described in Table Local blade characteristics for a given design point LDP such as the lift coefficient can be prescribed by the line NEWT1LDP IFTP1 JSEGIX1 FNEWT1 KDPRPM1 KDPFL1 KDPXJ1 ITP1 ITP2 ITP3 CLAMP1 TOL1 where IFTP1 500 gt local lift coefficient 501 gt local axial induction factor 502 gt local airfoil angle of attack 504 gt local power coefficient 505 gt local power 506 gt local chord cl ft JSEGIX1 blade segment for specified parameter FNEWT1 value for specified parameter KDPRPM1 design point for rotor speed KDPFL1 design point for blade pitch KDPXJ1 design point for wind speed Again the parameters ITP1 etc are the same as previously described in Table 8 2 NEWT2

PROPID User Manual - UIUC Applied Aerodynamics Group

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