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GOE 517 AIRFOIL (goe517-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 517 AIRFOIL (goe517-il)
Reynolds number: 500,000
Max Cl/Cd: 103.03 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe517-il-500000.txt
Download as CSV file: xf-goe517-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 517 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3657   0.08617   0.08407  -0.0280   1.0000   0.0179
  -7.500  -0.3665   0.08330   0.08122  -0.0288   1.0000   0.0179
  -7.250  -0.3760   0.07883   0.07681  -0.0291   1.0000   0.0182
  -7.000  -0.3815   0.07656   0.07458  -0.0272   1.0000   0.0184
  -6.750  -0.3590   0.07281   0.07081  -0.0312   0.9972   0.0188
  -6.500  -0.3319   0.06877   0.06674  -0.0369   0.9931   0.0194
  -6.250  -0.3027   0.06427   0.06219  -0.0438   0.9876   0.0200
  -6.000  -0.2684   0.05916   0.05701  -0.0520   0.9835   0.0219
  -5.750  -0.2261   0.05330   0.05098  -0.0616   0.9753   0.0239
  -5.500  -0.1883   0.04756   0.04508  -0.0684   0.9713   0.0241
  -5.250  -0.1678   0.04124   0.03863  -0.0727   0.9628   0.0254
  -5.000  -0.1368   0.03874   0.03603  -0.0756   0.9575   0.0265
  -4.500  -0.0827   0.02317   0.01942  -0.0798   0.9354   0.0255
  -4.250  -0.0627   0.01606   0.01135  -0.0785   0.9249   0.0214
  -4.000  -0.0368   0.01410   0.00895  -0.0779   0.9152   0.0221
  -3.750  -0.0106   0.01291   0.00748  -0.0773   0.9054   0.0230
  -3.500   0.0163   0.01200   0.00631  -0.0768   0.8965   0.0246
  -3.250   0.0417   0.01091   0.00506  -0.0762   0.8866   0.0266
  -3.000   0.0677   0.01041   0.00446  -0.0756   0.8758   0.0285
  -2.750   0.0937   0.00998   0.00391  -0.0749   0.8645   0.0307
  -2.500   0.1191   0.00946   0.00327  -0.0741   0.8535   0.0341
  -2.250   0.1449   0.00917   0.00294  -0.0734   0.8425   0.0387
  -2.000   0.1704   0.00887   0.00256  -0.0727   0.8313   0.0441
  -1.750   0.1965   0.00873   0.00239  -0.0721   0.8198   0.0537
  -1.500   0.2222   0.00852   0.00220  -0.0714   0.8087   0.0713
  -1.250   0.2484   0.00847   0.00210  -0.0709   0.7966   0.0845
  -1.000   0.2747   0.00847   0.00205  -0.0704   0.7833   0.0942
  -0.750   0.3004   0.00834   0.00191  -0.0698   0.7699   0.1047
  -0.500   0.3263   0.00825   0.00180  -0.0692   0.7562   0.1150
  -0.250   0.3522   0.00818   0.00170  -0.0687   0.7410   0.1273
   0.000   0.3778   0.00810   0.00161  -0.0681   0.7243   0.1410
   0.250   0.4032   0.00801   0.00153  -0.0674   0.7047   0.1615
   0.500   0.4277   0.00787   0.00148  -0.0667   0.6827   0.2133
   0.750   0.5120   0.00610   0.00155  -0.0795   0.6536   1.0000
   1.000   0.5355   0.00623   0.00154  -0.0785   0.6297   1.0000
   1.250   0.5588   0.00639   0.00154  -0.0775   0.6079   1.0000
   1.500   0.5826   0.00654   0.00157  -0.0765   0.5899   1.0000
   1.750   0.6065   0.00669   0.00162  -0.0757   0.5748   1.0000
   2.000   0.6306   0.00684   0.00168  -0.0748   0.5614   1.0000
   2.250   0.6547   0.00700   0.00176  -0.0740   0.5487   1.0000
   2.500   0.6788   0.00716   0.00185  -0.0732   0.5366   1.0000
   2.750   0.7032   0.00730   0.00194  -0.0724   0.5250   1.0000
   3.000   0.7277   0.00743   0.00204  -0.0717   0.5134   1.0000
   3.250   0.7520   0.00758   0.00216  -0.0709   0.5009   1.0000
   3.500   0.7763   0.00772   0.00228  -0.0701   0.4872   1.0000
   3.750   0.8006   0.00787   0.00239  -0.0694   0.4723   1.0000
   4.000   0.8243   0.00804   0.00251  -0.0685   0.4518   1.0000
   4.250   0.8479   0.00823   0.00264  -0.0676   0.4258   1.0000
   4.500   0.8706   0.00848   0.00279  -0.0667   0.3966   1.0000
   4.750   0.8929   0.00880   0.00298  -0.0656   0.3699   1.0000
   5.000   0.9151   0.00913   0.00322  -0.0646   0.3497   1.0000
   5.250   0.9376   0.00945   0.00348  -0.0636   0.3297   1.0000
   5.500   0.9597   0.00980   0.00374  -0.0626   0.3096   1.0000
   5.750   0.9827   0.01009   0.00399  -0.0617   0.2947   1.0000
   6.000   1.0057   0.01038   0.00425  -0.0608   0.2794   1.0000
   6.250   1.0287   0.01067   0.00452  -0.0600   0.2630   1.0000
   6.500   1.0519   0.01094   0.00478  -0.0592   0.2452   1.0000
   6.750   1.0739   0.01132   0.00507  -0.0582   0.2216   1.0000
   7.000   1.0950   0.01179   0.00542  -0.0572   0.1869   1.0000
   7.250   1.1059   0.01321   0.00626  -0.0547   0.0916   1.0000
   7.500   1.1183   0.01454   0.00728  -0.0523   0.0418   1.0000
   7.750   1.1362   0.01534   0.00804  -0.0507   0.0298   1.0000
   8.000   1.1543   0.01608   0.00881  -0.0491   0.0253   1.0000
   8.250   1.1704   0.01698   0.00980  -0.0472   0.0225   1.0000
   8.500   1.1887   0.01762   0.01053  -0.0457   0.0207   1.0000
   8.750   1.2055   0.01836   0.01134  -0.0440   0.0190   1.0000
   9.000   1.2173   0.01945   0.01250  -0.0416   0.0176   1.0000
   9.250   1.2226   0.02096   0.01414  -0.0382   0.0165   1.0000
   9.500   1.2358   0.02179   0.01508  -0.0360   0.0160   1.0000
   9.750   1.2451   0.02272   0.01610  -0.0331   0.0154   1.0000
  10.000   1.2527   0.02374   0.01721  -0.0301   0.0148   1.0000
  10.250   1.2605   0.02479   0.01834  -0.0274   0.0142   1.0000
  10.500   1.2686   0.02585   0.01949  -0.0249   0.0135   1.0000
  10.750   1.2746   0.02712   0.02081  -0.0225   0.0129   1.0000
  11.000   1.2779   0.02881   0.02257  -0.0199   0.0124   1.0000
  11.250   1.2767   0.03176   0.02566  -0.0171   0.0119   1.0000
  11.500   1.2837   0.03344   0.02748  -0.0152   0.0117   1.0000
  11.750   1.2903   0.03513   0.02931  -0.0135   0.0115   1.0000
  12.000   1.2958   0.03689   0.03123  -0.0118   0.0112   1.0000
  12.250   1.3000   0.03892   0.03342  -0.0103   0.0110   1.0000
  12.500   1.3020   0.04152   0.03620  -0.0088   0.0110   1.0000
  12.750   1.3021   0.04400   0.03886  -0.0075   0.0107   1.0000
  13.000   1.3001   0.04683   0.04188  -0.0064   0.0105   1.0000
  13.250   1.2955   0.05006   0.04533  -0.0056   0.0104   1.0000
  13.500   1.2881   0.05374   0.04922  -0.0052   0.0103   1.0000
  13.750   1.2791   0.05768   0.05335  -0.0052   0.0102   1.0000
  14.000   1.2662   0.06241   0.05830  -0.0058   0.0103   1.0000
  14.250   1.2551   0.06692   0.06298  -0.0070   0.0101   1.0000
  14.500   1.2394   0.07252   0.06879  -0.0088   0.0102   1.0000
  14.750   1.2272   0.07771   0.07413  -0.0111   0.0100   1.0000
  15.000   1.2242   0.08148   0.07796  -0.0131   0.0096   1.0000
  15.250   1.1891   0.09175   0.08855  -0.0179   0.0100   1.0000
  15.500   1.1713   0.09916   0.09613  -0.0221   0.0100   1.0000
  15.750   1.1607   0.10545   0.10252  -0.0259   0.0098   1.0000
  16.000   1.1225   0.11856   0.11587  -0.0335   0.0105   1.0000
  16.250   1.0993   0.12891   0.12636  -0.0399   0.0108   1.0000
  16.500   1.0786   0.13938   0.13696  -0.0464   0.0108   1.0000
  16.750   1.0507   0.15234   0.15002  -0.0542   0.0113   1.0000
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