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GOE 565 AIRFOIL (goe565-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 565 AIRFOIL (goe565-il)
Reynolds number: 500,000
Max Cl/Cd: 98.73 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe565-il-500000.txt
Download as CSV file: xf-goe565-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 565 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4422   0.08955   0.08721  -0.0311   1.0000   0.0269
  -9.000  -0.4435   0.08604   0.08373  -0.0322   1.0000   0.0277
  -8.750  -0.7004   0.03033   0.02709  -0.0550   1.0000   0.0168
  -8.500  -0.6998   0.02577   0.02197  -0.0533   1.0000   0.0174
  -8.250  -0.6722   0.02312   0.01886  -0.0551   0.9979   0.0185
  -8.000  -0.6448   0.02042   0.01574  -0.0567   0.9957   0.0198
  -7.750  -0.6114   0.02011   0.01540  -0.0583   0.9941   0.0207
  -7.500  -0.5815   0.01946   0.01463  -0.0591   0.9917   0.0220
  -7.250  -0.5511   0.01836   0.01327  -0.0601   0.9892   0.0235
  -7.000  -0.5206   0.01687   0.01154  -0.0612   0.9869   0.0252
  -6.750  -0.4854   0.01706   0.01177  -0.0629   0.9851   0.0269
  -6.500  -0.4502   0.01688   0.01150  -0.0646   0.9837   0.0292
  -6.250  -0.4216   0.01591   0.01033  -0.0650   0.9808   0.0315
  -6.000  -0.3911   0.01557   0.01001  -0.0658   0.9776   0.0336
  -5.750  -0.3572   0.01551   0.00990  -0.0672   0.9751   0.0363
  -5.500  -0.3217   0.01548   0.00976  -0.0687   0.9732   0.0386
  -5.250  -0.2893   0.01398   0.00816  -0.0701   0.9717   0.0417
  -5.000  -0.2533   0.01368   0.00783  -0.0720   0.9705   0.0445
  -4.750  -0.2256   0.01333   0.00743  -0.0719   0.9659   0.0469
  -4.500  -0.1919   0.01308   0.00711  -0.0731   0.9628   0.0489
  -4.250  -0.1570   0.01205   0.00599  -0.0747   0.9605   0.0512
  -4.000  -0.1194   0.01133   0.00527  -0.0768   0.9587   0.0543
  -3.750  -0.0816   0.01082   0.00474  -0.0788   0.9569   0.0567
  -3.500  -0.0523   0.01043   0.00432  -0.0790   0.9514   0.0586
  -3.250  -0.0209   0.01010   0.00395  -0.0796   0.9468   0.0608
  -3.000   0.0122   0.00971   0.00353  -0.0806   0.9436   0.0625
  -2.750   0.0415   0.00929   0.00310  -0.0807   0.9388   0.0662
  -2.500   0.0690   0.00903   0.00285  -0.0805   0.9323   0.0701
  -2.000   0.1259   0.00854   0.00238  -0.0802   0.9179   0.0861
  -1.750   0.1534   0.00820   0.00213  -0.0798   0.9087   0.1175
  -1.500   0.1783   0.00757   0.00194  -0.0792   0.8982   0.2485
  -1.250   0.2035   0.00731   0.00185  -0.0785   0.8874   0.3134
  -1.000   0.2298   0.00706   0.00176  -0.0781   0.8779   0.3712
  -0.750   0.2551   0.00669   0.00170  -0.0775   0.8679   0.4748
  -0.500   0.2785   0.00634   0.00171  -0.0764   0.8561   0.5943
  -0.250   0.3024   0.00607   0.00169  -0.0753   0.8445   0.6838
   0.000   0.3245   0.00570   0.00167  -0.0738   0.8330   0.7819
   0.250   0.3873   0.00537   0.00166  -0.0808   0.8239   0.9792
   0.500   0.4311   0.00539   0.00162  -0.0841   0.8103   1.0000
   0.750   0.4554   0.00545   0.00158  -0.0832   0.7929   1.0000
   1.000   0.4797   0.00552   0.00157  -0.0822   0.7748   1.0000
   1.250   0.5043   0.00561   0.00158  -0.0813   0.7581   1.0000
   1.500   0.5286   0.00572   0.00160  -0.0803   0.7397   1.0000
   1.750   0.5526   0.00585   0.00163  -0.0793   0.7198   1.0000
   2.000   0.5768   0.00597   0.00168  -0.0784   0.6995   1.0000
   2.250   0.6004   0.00612   0.00175  -0.0773   0.6761   1.0000
   2.500   0.6230   0.00631   0.00180  -0.0760   0.6384   1.0000
   2.750   0.6434   0.00662   0.00187  -0.0743   0.5826   1.0000
   3.000   0.6641   0.00699   0.00200  -0.0728   0.5332   1.0000
   3.250   0.6861   0.00732   0.00216  -0.0716   0.4946   1.0000
   3.500   0.7084   0.00766   0.00233  -0.0704   0.4548   1.0000
   3.750   0.7310   0.00800   0.00251  -0.0694   0.4144   1.0000
   4.000   0.7534   0.00837   0.00270  -0.0683   0.3731   1.0000
   4.250   0.7755   0.00879   0.00294  -0.0672   0.3318   1.0000
   4.500   0.7975   0.00924   0.00319  -0.0661   0.2875   1.0000
   4.750   0.8198   0.00968   0.00345  -0.0652   0.2459   1.0000
   5.000   0.8418   0.01017   0.00374  -0.0642   0.2055   1.0000
   5.250   0.8642   0.01062   0.00406  -0.0632   0.1795   1.0000
   5.500   0.8873   0.01102   0.00438  -0.0624   0.1597   1.0000
   5.750   0.9101   0.01145   0.00470  -0.0615   0.1345   1.0000
   6.000   0.9283   0.01236   0.00522  -0.0599   0.0658   1.0000
   6.250   0.9489   0.01304   0.00577  -0.0587   0.0465   1.0000
   6.500   0.9713   0.01353   0.00627  -0.0577   0.0419   1.0000
   6.750   0.9917   0.01424   0.00700  -0.0563   0.0372   1.0000
   7.000   1.0141   0.01469   0.00752  -0.0553   0.0354   1.0000
   7.250   1.0353   0.01525   0.00815  -0.0542   0.0330   1.0000
   7.500   1.0544   0.01602   0.00895  -0.0527   0.0304   1.0000
   7.750   1.0701   0.01712   0.01013  -0.0507   0.0282   1.0000
   8.000   1.0912   0.01766   0.01074  -0.0496   0.0269   1.0000
   8.250   1.1110   0.01831   0.01144  -0.0482   0.0252   1.0000
   8.500   1.1299   0.01901   0.01218  -0.0469   0.0236   1.0000
   8.750   1.1413   0.02060   0.01382  -0.0445   0.0219   1.0000
   9.000   1.1601   0.02134   0.01465  -0.0430   0.0210   1.0000
   9.250   1.1786   0.02208   0.01548  -0.0416   0.0201   1.0000
   9.500   1.1959   0.02294   0.01642  -0.0400   0.0192   1.0000
   9.750   1.2127   0.02374   0.01730  -0.0384   0.0183   1.0000
  10.000   1.2283   0.02456   0.01815  -0.0368   0.0175   1.0000
  10.250   1.2387   0.02658   0.02022  -0.0346   0.0165   1.0000
  10.500   1.2514   0.02759   0.02138  -0.0324   0.0160   1.0000
  10.750   1.2634   0.02864   0.02256  -0.0302   0.0156   1.0000
  11.000   1.2742   0.02977   0.02383  -0.0279   0.0150   1.0000
  11.250   1.2837   0.03105   0.02524  -0.0256   0.0145   1.0000
  11.500   1.2918   0.03245   0.02678  -0.0233   0.0141   1.0000
  11.750   1.2983   0.03383   0.02828  -0.0210   0.0137   1.0000
  12.000   1.3040   0.03507   0.02962  -0.0188   0.0134   1.0000
  12.250   1.3081   0.03670   0.03135  -0.0166   0.0131   1.0000
  12.500   1.3105   0.03861   0.03337  -0.0146   0.0129   1.0000
  12.750   1.3076   0.04144   0.03636  -0.0126   0.0126   1.0000
  13.250   1.2864   0.04857   0.04398  -0.0090   0.0122   1.0000
  13.500   1.2778   0.05171   0.04732  -0.0081   0.0121   1.0000
  13.750   1.2686   0.05508   0.05090  -0.0078   0.0120   1.0000
  14.000   1.2549   0.05944   0.05548  -0.0083   0.0118   1.0000
  14.250   1.2387   0.06458   0.06082  -0.0096   0.0118   1.0000
  14.500   1.2217   0.07026   0.06671  -0.0118   0.0117   1.0000
  14.750   1.1996   0.07737   0.07401  -0.0151   0.0119   1.0000
  15.000   1.1818   0.08435   0.08118  -0.0192   0.0117   1.0000
  15.250   1.1598   0.09278   0.08978  -0.0244   0.0118   1.0000
  15.500   1.1327   0.10293   0.10010  -0.0307   0.0120   1.0000
  15.750   1.1084   0.11319   0.11051  -0.0372   0.0121   1.0000
  16.000   1.0797   0.12510   0.12255  -0.0447   0.0123   1.0000
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