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GOE 502 AIRFOIL (goe502-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 502 AIRFOIL (goe502-il)
Reynolds number: 500,000
Max Cl/Cd: 106.74 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe502-il-500000.txt
Download as CSV file: xf-goe502-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 502 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.4054   0.04910   0.04577  -0.1380   0.9648   0.0432
 -11.500  -0.4335   0.03552   0.03165  -0.1627   0.9547   0.0430
 -11.250  -0.4263   0.03214   0.02801  -0.1674   0.9462   0.0432
 -11.000  -0.4029   0.02956   0.02519  -0.1718   0.9420   0.0436
 -10.750  -0.3742   0.02744   0.02284  -0.1757   0.9388   0.0441
 -10.500  -0.3601   0.02615   0.02138  -0.1753   0.9298   0.0445
 -10.250  -0.3326   0.02476   0.01975  -0.1772   0.9244   0.0450
 -10.000  -0.3119   0.02371   0.01850  -0.1773   0.9165   0.0454
  -9.750  -0.2881   0.02286   0.01743  -0.1775   0.9087   0.0457
  -9.500  -0.2644   0.02121   0.01567  -0.1779   0.9018   0.0461
  -9.250  -0.2439   0.02017   0.01461  -0.1771   0.8932   0.0466
  -9.000  -0.2160   0.01935   0.01372  -0.1777   0.8871   0.0472
  -8.750  -0.1959   0.01872   0.01304  -0.1766   0.8783   0.0476
  -8.500  -0.1706   0.01807   0.01231  -0.1764   0.8706   0.0482
  -8.250  -0.1472   0.01748   0.01166  -0.1758   0.8622   0.0488
  -8.000  -0.1232   0.01692   0.01101  -0.1753   0.8533   0.0495
  -7.750  -0.0979   0.01644   0.01043  -0.1749   0.8452   0.0502
  -7.500  -0.0735   0.01607   0.00995  -0.1743   0.8355   0.0508
  -7.250  -0.0489   0.01542   0.00921  -0.1739   0.8269   0.0515
  -7.000  -0.0258   0.01470   0.00849  -0.1732   0.8171   0.0523
  -6.750  -0.0006   0.01422   0.00798  -0.1728   0.8088   0.0531
  -6.500   0.0241   0.01381   0.00753  -0.1723   0.7998   0.0539
  -6.250   0.0503   0.01345   0.00709  -0.1719   0.7920   0.0549
  -6.000   0.0755   0.01313   0.00671  -0.1714   0.7835   0.0558
  -5.750   0.1022   0.01288   0.00635  -0.1711   0.7759   0.0567
  -5.500   0.1268   0.01244   0.00588  -0.1706   0.7686   0.0578
  -5.250   0.1523   0.01205   0.00547  -0.1702   0.7617   0.0593
  -5.000   0.1792   0.01180   0.00515  -0.1700   0.7554   0.0608
  -4.750   0.2049   0.01157   0.00488  -0.1695   0.7486   0.0623
  -4.500   0.2317   0.01139   0.00462  -0.1692   0.7420   0.0636
  -4.250   0.2585   0.01110   0.00429  -0.1690   0.7360   0.0659
  -4.000   0.2845   0.01088   0.00406  -0.1685   0.7300   0.0684
  -3.750   0.3113   0.01071   0.00384  -0.1682   0.7238   0.0719
  -3.500   0.3391   0.01055   0.00365  -0.1681   0.7176   0.0788
  -3.250   0.3642   0.01024   0.00351  -0.1676   0.7116   0.1079
  -3.000   0.3905   0.01006   0.00342  -0.1672   0.7055   0.1395
  -2.750   0.4182   0.01000   0.00337  -0.1670   0.6993   0.1617
  -2.500   0.4442   0.00993   0.00335  -0.1665   0.6931   0.1767
  -2.250   0.4705   0.00988   0.00332  -0.1660   0.6863   0.1903
  -2.000   0.4979   0.00991   0.00329  -0.1657   0.6799   0.2016
  -1.750   0.5237   0.00986   0.00329  -0.1652   0.6733   0.2135
  -1.500   0.5497   0.00983   0.00327  -0.1646   0.6659   0.2248
  -1.250   0.5764   0.00989   0.00327  -0.1642   0.6589   0.2370
  -1.000   0.6016   0.00983   0.00328  -0.1634   0.6512   0.2481
  -0.750   0.6273   0.00986   0.00326  -0.1628   0.6433   0.2582
  -0.500   0.6527   0.00986   0.00328  -0.1621   0.6352   0.2692
  -0.250   0.6778   0.00988   0.00328  -0.1614   0.6263   0.2791
   0.000   0.7029   0.00991   0.00331  -0.1606   0.6182   0.2897
   0.250   0.7277   0.00994   0.00332  -0.1598   0.6090   0.2990
   0.500   0.7521   0.00999   0.00335  -0.1590   0.6005   0.3089
   0.750   0.7767   0.01005   0.00338  -0.1581   0.5915   0.3181
   1.000   0.8008   0.01011   0.00344  -0.1572   0.5835   0.3291
   1.250   0.8255   0.01017   0.00350  -0.1565   0.5754   0.3399
   1.500   0.8493   0.01026   0.00357  -0.1555   0.5676   0.3513
   1.750   0.8739   0.01034   0.00365  -0.1548   0.5605   0.3618
   2.000   0.8981   0.01042   0.00374  -0.1539   0.5536   0.3739
   2.250   0.9221   0.01056   0.00385  -0.1531   0.5471   0.3869
   2.500   0.9466   0.01062   0.00396  -0.1523   0.5410   0.4019
   2.750   0.9704   0.01072   0.00408  -0.1514   0.5347   0.4181
   3.000   0.9947   0.01088   0.00423  -0.1506   0.5289   0.4359
   3.250   1.0187   0.01093   0.00437  -0.1497   0.5239   0.4551
   3.500   1.0420   0.01101   0.00450  -0.1488   0.5182   0.4765
   3.750   1.0646   0.01116   0.00464  -0.1477   0.5120   0.4998
   4.000   1.0858   0.01120   0.00479  -0.1463   0.5059   0.5281
   4.250   1.1059   0.01120   0.00494  -0.1447   0.4999   0.5737
   4.500   1.1244   0.01113   0.00517  -0.1428   0.4945   0.6990
   4.750   1.1593   0.01092   0.00542  -0.1442   0.4889   1.0000
   5.000   1.1804   0.01106   0.00556  -0.1428   0.4834   1.0000
   5.250   1.2008   0.01126   0.00571  -0.1413   0.4773   1.0000
   5.500   1.2228   0.01152   0.00590  -0.1401   0.4719   1.0000
   5.750   1.2439   0.01166   0.00608  -0.1388   0.4673   1.0000
   6.000   1.2649   0.01185   0.00626  -0.1374   0.4621   1.0000
   6.250   1.2847   0.01210   0.00646  -0.1359   0.4563   1.0000
   6.500   1.3047   0.01231   0.00668  -0.1344   0.4507   1.0000
   6.750   1.3246   0.01251   0.00689  -0.1329   0.4449   1.0000
   7.000   1.3434   0.01277   0.00712  -0.1313   0.4391   1.0000
   7.250   1.3626   0.01304   0.00738  -0.1297   0.4335   1.0000
   7.500   1.3824   0.01326   0.00763  -0.1283   0.4280   1.0000
   7.750   1.4008   0.01354   0.00790  -0.1266   0.4223   1.0000
   8.000   1.4179   0.01388   0.00822  -0.1248   0.4160   1.0000
   8.250   1.4358   0.01415   0.00852  -0.1232   0.4086   1.0000
   8.500   1.4506   0.01456   0.00889  -0.1210   0.4014   1.0000
   8.750   1.4683   0.01488   0.00925  -0.1194   0.3941   1.0000
   9.000   1.4840   0.01529   0.00965  -0.1175   0.3868   1.0000
   9.250   1.4994   0.01574   0.01009  -0.1156   0.3799   1.0000
   9.500   1.5154   0.01617   0.01055  -0.1139   0.3719   1.0000
   9.750   1.5280   0.01675   0.01111  -0.1117   0.3637   1.0000
  10.000   1.5422   0.01729   0.01166  -0.1098   0.3535   1.0000
  10.250   1.5544   0.01795   0.01230  -0.1077   0.3446   1.0000
  10.500   1.5657   0.01867   0.01301  -0.1055   0.3337   1.0000
  10.750   1.5769   0.01943   0.01376  -0.1034   0.3224   1.0000
  11.000   1.5850   0.02038   0.01467  -0.1010   0.3097   1.0000
  11.250   1.5915   0.02146   0.01571  -0.0985   0.2960   1.0000
  11.500   1.5959   0.02273   0.01693  -0.0960   0.2800   1.0000
  11.750   1.5994   0.02411   0.01826  -0.0934   0.2635   1.0000
  12.000   1.6010   0.02570   0.01978  -0.0909   0.2455   1.0000
  12.250   1.5999   0.02757   0.02157  -0.0883   0.2266   1.0000
  12.500   1.5974   0.02964   0.02356  -0.0858   0.2094   1.0000
  12.750   1.5957   0.03177   0.02565  -0.0836   0.1958   1.0000
  13.000   1.5943   0.03398   0.02782  -0.0816   0.1851   1.0000
  13.250   1.5958   0.03602   0.02986  -0.0800   0.1768   1.0000
  13.500   1.5968   0.03819   0.03203  -0.0784   0.1703   1.0000
  13.750   1.6001   0.04021   0.03407  -0.0771   0.1647   1.0000
  14.000   1.5993   0.04263   0.03649  -0.0757   0.1593   1.0000
  14.250   1.6044   0.04457   0.03849  -0.0747   0.1548   1.0000
  14.500   1.6070   0.04679   0.04074  -0.0736   0.1501   1.0000
  14.750   1.6058   0.04942   0.04339  -0.0725   0.1455   1.0000
  15.000   1.6104   0.05153   0.04556  -0.0717   0.1415   1.0000
  15.250   1.6137   0.05381   0.04789  -0.0710   0.1371   1.0000
  15.500   1.6116   0.05672   0.05080  -0.0702   0.1325   1.0000
  15.750   1.6152   0.05908   0.05324  -0.0697   0.1282   1.0000
  16.000   1.6166   0.06173   0.05592  -0.0692   0.1232   1.0000
  16.250   1.6138   0.06488   0.05909  -0.0688   0.1182   1.0000
  16.500   1.6157   0.06757   0.06183  -0.0685   0.1125   1.0000
  16.750   1.6110   0.07111   0.06538  -0.0683   0.1068   1.0000
  17.000   1.6104   0.07418   0.06849  -0.0682   0.1004   1.0000
  17.250   1.6055   0.07784   0.07217  -0.0682   0.0940   1.0000
  17.500   1.5987   0.08181   0.07614  -0.0683   0.0881   1.0000
  17.750   1.5953   0.08537   0.07973  -0.0685   0.0828   1.0000
  18.000   1.5882   0.08950   0.08387  -0.0689   0.0784   1.0000
  18.250   1.5851   0.09312   0.08754  -0.0693   0.0750   1.0000
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