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GOE 529 AIRFOIL (goe529-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 529 AIRFOIL (goe529-il)
Reynolds number: 500,000
Max Cl/Cd: 114.6 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe529-il-500000.txt
Download as CSV file: xf-goe529-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 529 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2511   0.10715   0.10495  -0.0364   1.0000   0.0210
  -9.500  -0.2560   0.10445   0.10230  -0.0383   1.0000   0.0217
  -9.250  -0.2614   0.10207   0.09996  -0.0387   1.0000   0.0218
  -9.000  -0.2564   0.09861   0.09653  -0.0413   0.9987   0.0219
  -8.750  -0.2389   0.09398   0.09190  -0.0468   0.9928   0.0220
  -8.500  -0.2217   0.08988   0.08780  -0.0468   0.9887   0.0226
  -8.250  -0.2023   0.08646   0.08438  -0.0505   0.9814   0.0230
  -8.000  -0.1819   0.08325   0.08116  -0.0546   0.9719   0.0242
  -7.750  -0.1593   0.07897   0.07686  -0.0611   0.9609   0.0257
  -7.500  -0.0753   0.05501   0.05268  -0.0794   0.8628   0.0276
  -7.250  -0.0715   0.05210   0.04968  -0.0781   0.8386   0.0281
  -7.000  -0.0872   0.06158   0.05921  -0.0917   0.8900   0.0281
  -6.750  -0.0719   0.05988   0.05738  -0.0917   0.8629   0.0287
  -6.500  -0.0590   0.05802   0.05537  -0.0923   0.8363   0.0297
  -6.250  -0.0467   0.05536   0.05258  -0.0942   0.8121   0.0310
  -6.000  -0.0239   0.05009   0.04706  -0.1020   0.7912   0.0341
  -5.750  -0.0143   0.04310   0.03985  -0.1058   0.7746   0.0348
  -5.500   0.0012   0.04160   0.03826  -0.1054   0.7583   0.0356
  -5.250   0.0199   0.04020   0.03675  -0.1054   0.7435   0.0365
  -5.000   0.0405   0.03834   0.03477  -0.1060   0.7305   0.0382
  -4.750   0.0648   0.03077   0.02666  -0.1098   0.7206   0.0439
  -4.500   0.0860   0.02984   0.02567  -0.1095   0.7107   0.0448
  -4.250   0.1086   0.02875   0.02447  -0.1094   0.7016   0.0462
  -4.000   0.1300   0.02056   0.01524  -0.1096   0.6955   0.0434
  -3.750   0.1521   0.01736   0.01169  -0.1091   0.6884   0.0397
  -3.500   0.1768   0.01536   0.00927  -0.1085   0.6823   0.0395
  -3.250   0.2030   0.01442   0.00809  -0.1081   0.6759   0.0406
  -3.000   0.2293   0.01355   0.00697  -0.1077   0.6702   0.0411
  -2.750   0.2561   0.01284   0.00610  -0.1074   0.6644   0.0415
  -2.500   0.2829   0.01229   0.00541  -0.1070   0.6588   0.0420
  -2.250   0.3099   0.01192   0.00490  -0.1067   0.6539   0.0426
  -2.000   0.3363   0.01116   0.00406  -0.1064   0.6488   0.0440
  -1.750   0.3628   0.01074   0.00359  -0.1060   0.6435   0.0454
  -1.500   0.3896   0.01052   0.00330  -0.1057   0.6386   0.0468
  -1.250   0.4167   0.01030   0.00308  -0.1054   0.6336   0.0485
  -1.000   0.4437   0.01014   0.00288  -0.1051   0.6285   0.0505
  -0.750   0.4708   0.01006   0.00273  -0.1048   0.6236   0.0527
  -0.500   0.4976   0.00983   0.00255  -0.1046   0.6183   0.0589
  -0.250   0.5246   0.00970   0.00244  -0.1043   0.6131   0.0704
   0.000   0.5514   0.00962   0.00240  -0.1040   0.6080   0.1019
   0.250   0.5784   0.00952   0.00238  -0.1038   0.6023   0.1253
   0.500   0.6053   0.00947   0.00238  -0.1035   0.5966   0.1510
   0.750   0.6320   0.00942   0.00240  -0.1033   0.5908   0.1866
   1.000   0.6578   0.00916   0.00242  -0.1030   0.5836   0.2809
   1.250   0.7048   0.00764   0.00252  -0.1074   0.5745   1.0000
   1.500   0.7303   0.00769   0.00250  -0.1069   0.5660   1.0000
   1.750   0.7559   0.00776   0.00250  -0.1063   0.5577   1.0000
   2.000   0.7814   0.00783   0.00250  -0.1057   0.5491   1.0000
   2.250   0.8073   0.00789   0.00253  -0.1053   0.5403   1.0000
   2.500   0.8327   0.00800   0.00256  -0.1047   0.5322   1.0000
   2.750   0.8586   0.00807   0.00261  -0.1043   0.5227   1.0000
   3.000   0.8842   0.00817   0.00266  -0.1038   0.5132   1.0000
   3.250   0.9093   0.00830   0.00273  -0.1032   0.5031   1.0000
   3.500   0.9348   0.00842   0.00281  -0.1027   0.4922   1.0000
   3.750   0.9600   0.00856   0.00291  -0.1022   0.4818   1.0000
   4.000   0.9848   0.00873   0.00303  -0.1016   0.4722   1.0000
   4.250   1.0098   0.00890   0.00317  -0.1011   0.4624   1.0000
   4.500   1.0348   0.00908   0.00331  -0.1006   0.4534   1.0000
   5.000   1.0843   0.00947   0.00366  -0.0995   0.4359   1.0000
   5.250   1.1087   0.00969   0.00384  -0.0989   0.4274   1.0000
   5.500   1.1334   0.00989   0.00404  -0.0984   0.4194   1.0000
   5.750   1.1578   0.01011   0.00425  -0.0978   0.4119   1.0000
   6.000   1.1814   0.01035   0.00447  -0.0971   0.4013   1.0000
   6.250   1.2046   0.01060   0.00468  -0.0964   0.3869   1.0000
   6.500   1.2282   0.01083   0.00490  -0.0957   0.3743   1.0000
   6.750   1.2516   0.01107   0.00513  -0.0950   0.3628   1.0000
   7.000   1.2745   0.01134   0.00539  -0.0942   0.3506   1.0000
   7.250   1.2967   0.01163   0.00566  -0.0934   0.3360   1.0000
   7.500   1.3185   0.01195   0.00595  -0.0924   0.3203   1.0000
   7.750   1.3393   0.01231   0.00627  -0.0913   0.3032   1.0000
   8.000   1.3580   0.01279   0.00667  -0.0899   0.2826   1.0000
   8.250   1.3762   0.01329   0.00709  -0.0885   0.2602   1.0000
   8.500   1.3914   0.01395   0.00762  -0.0866   0.2338   1.0000
   8.750   1.4022   0.01483   0.00829  -0.0840   0.1986   1.0000
   9.000   1.4005   0.01623   0.00930  -0.0795   0.1364   1.0000
   9.250   1.4007   0.01741   0.01032  -0.0752   0.1097   1.0000
   9.500   1.3996   0.01872   0.01142  -0.0711   0.0703   1.0000
   9.750   1.3906   0.02054   0.01300  -0.0662   0.0357   1.0000
  10.000   1.3914   0.02194   0.01433  -0.0629   0.0230   1.0000
  10.250   1.3970   0.02315   0.01557  -0.0605   0.0203   1.0000
  10.500   1.4023   0.02446   0.01696  -0.0582   0.0187   1.0000
  10.750   1.4093   0.02572   0.01832  -0.0563   0.0180   1.0000
  11.000   1.4143   0.02721   0.01992  -0.0544   0.0171   1.0000
  11.250   1.4170   0.02897   0.02177  -0.0527   0.0162   1.0000
  11.500   1.4172   0.03105   0.02394  -0.0510   0.0155   1.0000
  11.750   1.4157   0.03342   0.02641  -0.0495   0.0151   1.0000
  12.000   1.4095   0.03638   0.02950  -0.0481   0.0146   1.0000
  12.250   1.4069   0.03915   0.03238  -0.0471   0.0143   1.0000
  12.500   1.4073   0.04171   0.03504  -0.0465   0.0141   1.0000
  12.750   1.4058   0.04456   0.03800  -0.0459   0.0138   1.0000
  13.000   1.4044   0.04745   0.04099  -0.0454   0.0136   1.0000
  13.250   1.4006   0.05072   0.04436  -0.0451   0.0133   1.0000
  13.500   1.3969   0.05403   0.04777  -0.0449   0.0131   1.0000
  13.750   1.3931   0.05744   0.05128  -0.0448   0.0129   1.0000
  14.000   1.3899   0.06089   0.05483  -0.0449   0.0127   1.0000
  14.250   1.3867   0.06440   0.05842  -0.0451   0.0125   1.0000
  14.500   1.3831   0.06802   0.06213  -0.0453   0.0123   1.0000
  14.750   1.3808   0.07157   0.06576  -0.0456   0.0121   1.0000
  15.000   1.3785   0.07514   0.06940  -0.0460   0.0118   1.0000
  15.250   1.3761   0.07872   0.07302  -0.0465   0.0115   1.0000
  15.500   1.3735   0.08207   0.07641  -0.0463   0.0112   1.0000
  15.750   1.3752   0.08471   0.07911  -0.0457   0.0109   1.0000
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