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GOE 510 AIRFOIL (goe510-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 510 AIRFOIL (goe510-il)
Reynolds number: 500,000
Max Cl/Cd: 82.38 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe510-il-500000-n5.txt
Download as CSV file: xf-goe510-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 510 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.1194   0.09407   0.09140  -0.0937   0.9659   0.0283
 -10.500  -0.1095   0.09097   0.08829  -0.0960   0.9630   0.0284
  -9.500  -0.3443   0.03036   0.02667  -0.1300   0.9208   0.0327
  -9.250  -0.3257   0.02836   0.02448  -0.1304   0.9154   0.0329
  -9.000  -0.3001   0.02693   0.02290  -0.1314   0.9111   0.0332
  -8.500  -0.2622   0.02421   0.01982  -0.1302   0.8962   0.0337
  -8.250  -0.2454   0.02320   0.01865  -0.1287   0.8866   0.0341
  -8.000  -0.2196   0.02193   0.01717  -0.1292   0.8804   0.0345
  -7.750  -0.2007   0.02089   0.01594  -0.1280   0.8711   0.0351
  -7.500  -0.1769   0.01967   0.01446  -0.1278   0.8627   0.0356
  -7.250  -0.1544   0.01853   0.01307  -0.1272   0.8519   0.0361
  -7.000  -0.1319   0.01764   0.01196  -0.1263   0.8412   0.0365
  -6.750  -0.1069   0.01690   0.01099  -0.1259   0.8316   0.0369
  -6.500  -0.0839   0.01632   0.01022  -0.1250   0.8202   0.0372
  -6.250  -0.0616   0.01566   0.00944  -0.1240   0.8090   0.0376
  -6.000  -0.0380   0.01526   0.00894  -0.1232   0.7962   0.0380
  -5.750  -0.0151   0.01495   0.00853  -0.1222   0.7839   0.0383
  -5.500   0.0073   0.01465   0.00815  -0.1210   0.7726   0.0387
  -5.250   0.0301   0.01439   0.00780  -0.1199   0.7615   0.0391
  -5.000   0.0525   0.01416   0.00748  -0.1187   0.7494   0.0396
  -4.750   0.0743   0.01391   0.00714  -0.1173   0.7362   0.0401
  -4.500   0.0958   0.01370   0.00682  -0.1159   0.7219   0.0408
  -4.250   0.1166   0.01343   0.00643  -0.1143   0.7067   0.0413
  -4.000   0.1372   0.01322   0.00609  -0.1127   0.6914   0.0418
  -3.750   0.1578   0.01302   0.00578  -0.1111   0.6775   0.0422
  -3.250   0.1997   0.01274   0.00529  -0.1079   0.6518   0.0430
  -3.000   0.2198   0.01243   0.00493  -0.1063   0.6396   0.0437
  -2.750   0.2400   0.01228   0.00472  -0.1046   0.6280   0.0442
  -2.500   0.2606   0.01218   0.00456  -0.1030   0.6158   0.0448
  -2.250   0.2819   0.01208   0.00442  -0.1015   0.6055   0.0456
  -2.000   0.3021   0.01202   0.00430  -0.0998   0.5948   0.0464
  -1.750   0.3228   0.01192   0.00415  -0.0982   0.5832   0.0472
  -1.500   0.3416   0.01184   0.00401  -0.0962   0.5711   0.0478
  -1.250   0.3594   0.01178   0.00388  -0.0940   0.5581   0.0485
  -1.000   0.3772   0.01174   0.00377  -0.0918   0.5441   0.0491
  -0.750   0.3952   0.01172   0.00368  -0.0896   0.5284   0.0496
  -0.500   0.4121   0.01166   0.00356  -0.0872   0.5118   0.0504
  -0.250   0.4285   0.01163   0.00346  -0.0848   0.4949   0.0513
   0.000   0.4461   0.01165   0.00342  -0.0826   0.4800   0.0525
   0.250   0.4648   0.01169   0.00340  -0.0807   0.4677   0.0537
   0.500   0.4833   0.01175   0.00340  -0.0787   0.4560   0.0550
   0.750   0.5027   0.01182   0.00342  -0.0770   0.4460   0.0560
   1.000   0.5227   0.01188   0.00343  -0.0753   0.4381   0.0569
   1.250   0.5429   0.01195   0.00346  -0.0737   0.4306   0.0579
   1.500   0.5625   0.01201   0.00348  -0.0720   0.4240   0.0598
   1.750   0.5834   0.01205   0.00351  -0.0706   0.4175   0.0619
   2.000   0.6036   0.01213   0.00357  -0.0690   0.4118   0.0648
   2.250   0.6238   0.01221   0.00363  -0.0675   0.4064   0.0681
   2.500   0.6449   0.01224   0.00369  -0.0661   0.4021   0.0763
   2.750   0.6622   0.01212   0.00381  -0.0640   0.3972   0.1589
   3.000   0.6808   0.01217   0.00397  -0.0623   0.3925   0.2050
   3.250   0.7019   0.01225   0.00410  -0.0609   0.3887   0.2299
   3.500   0.7234   0.01233   0.00422  -0.0597   0.3844   0.2479
   3.750   0.7439   0.01245   0.00437  -0.0583   0.3797   0.2653
   4.000   0.7637   0.01259   0.00452  -0.0568   0.3758   0.2779
   4.250   0.7844   0.01272   0.00465  -0.0555   0.3724   0.2874
   4.500   0.8060   0.01281   0.00479  -0.0543   0.3688   0.2990
   4.750   0.8265   0.01292   0.00494  -0.0530   0.3644   0.3124
   5.000   0.8460   0.01306   0.00510  -0.0515   0.3603   0.3296
   5.250   0.8646   0.01321   0.00528  -0.0498   0.3562   0.3489
   5.500   0.8845   0.01325   0.00545  -0.0484   0.3527   0.3858
   6.000   1.0535   0.01300   0.00653  -0.0740   0.3393   0.9911
   6.250   1.0859   0.01328   0.00681  -0.0753   0.3340   0.9983
   6.500   1.1163   0.01355   0.00706  -0.0763   0.3292   1.0000
   6.750   1.1305   0.01378   0.00727  -0.0738   0.3252   1.0000
   7.000   1.1464   0.01399   0.00748  -0.0717   0.3208   1.0000
   7.250   1.1624   0.01421   0.00770  -0.0696   0.3153   1.0000
   7.500   1.1755   0.01454   0.00798  -0.0671   0.3073   1.0000
   7.750   1.1921   0.01479   0.00823  -0.0652   0.3003   1.0000
   8.000   1.2051   0.01518   0.00856  -0.0628   0.2917   1.0000
   8.250   1.2210   0.01550   0.00888  -0.0609   0.2825   1.0000
   8.500   1.2346   0.01593   0.00927  -0.0587   0.2738   1.0000
   8.750   1.2479   0.01641   0.00969  -0.0565   0.2628   1.0000
   9.000   1.2605   0.01694   0.01016  -0.0543   0.2499   1.0000
   9.250   1.2728   0.01751   0.01069  -0.0521   0.2388   1.0000
   9.500   1.2847   0.01813   0.01126  -0.0499   0.2283   1.0000
   9.750   1.2975   0.01874   0.01184  -0.0479   0.2184   1.0000
  10.000   1.3090   0.01943   0.01249  -0.0458   0.2072   1.0000
  10.250   1.3183   0.02027   0.01327  -0.0436   0.1940   1.0000
  10.500   1.3223   0.02144   0.01431  -0.0407   0.1724   1.0000
  10.750   1.3281   0.02256   0.01534  -0.0383   0.1556   1.0000
  11.000   1.3264   0.02419   0.01681  -0.0351   0.1302   1.0000
  11.250   1.3245   0.02592   0.01842  -0.0322   0.1086   1.0000
  11.500   1.3196   0.02795   0.02034  -0.0292   0.0877   1.0000
  11.750   1.3123   0.03027   0.02255  -0.0263   0.0657   1.0000
  12.250   1.2913   0.03594   0.02813  -0.0210   0.0208   1.0000
  12.500   1.2963   0.03770   0.02995  -0.0198   0.0191   1.0000
  12.750   1.3006   0.03959   0.03190  -0.0187   0.0178   1.0000
  13.000   1.3056   0.04146   0.03384  -0.0178   0.0170   1.0000
  13.250   1.3101   0.04344   0.03590  -0.0170   0.0163   1.0000
  13.500   1.3134   0.04560   0.03813  -0.0162   0.0156   1.0000
  13.750   1.3162   0.04788   0.04049  -0.0156   0.0153   1.0000
  14.000   1.3167   0.05044   0.04314  -0.0150   0.0147   1.0000
  14.250   1.3158   0.05322   0.04600  -0.0145   0.0143   1.0000
  14.500   1.3149   0.05607   0.04895  -0.0141   0.0139   1.0000
  14.750   1.3152   0.05885   0.05182  -0.0139   0.0136   1.0000
  15.000   1.3141   0.06186   0.05491  -0.0138   0.0134   1.0000
  15.250   1.3127   0.06494   0.05809  -0.0138   0.0130   1.0000
  15.500   1.3092   0.06834   0.06159  -0.0138   0.0128   1.0000
  15.750   1.3045   0.07198   0.06532  -0.0141   0.0125   1.0000
  16.000   1.2998   0.07570   0.06914  -0.0144   0.0123   1.0000
  16.250   1.2941   0.07959   0.07312  -0.0149   0.0121   1.0000
  16.500   1.2873   0.08366   0.07728  -0.0155   0.0119   1.0000
  16.750   1.2791   0.08798   0.08170  -0.0162   0.0116   1.0000
  17.000   1.2718   0.09225   0.08607  -0.0169   0.0116   1.0000
  17.250   1.2630   0.09675   0.09066  -0.0178   0.0115   1.0000
  17.500   1.2513   0.10172   0.09573  -0.0189   0.0113   1.0000
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