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GOE 369 AIRFOIL (goe369-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 369 AIRFOIL (goe369-il)
Reynolds number: 500,000
Max Cl/Cd: 105.86 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe369-il-500000.txt
Download as CSV file: xf-goe369-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 369 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2731   0.08321   0.08115  -0.0146   1.0000   0.0098
  -8.000  -0.2692   0.07995   0.07792  -0.0149   1.0000   0.0100
  -7.750  -0.2658   0.07687   0.07487  -0.0155   1.0000   0.0101
  -7.500  -0.3475   0.08902   0.08691  -0.0132   1.0000   0.0096
  -7.250  -0.3420   0.08577   0.08368  -0.0129   1.0000   0.0098
  -7.000  -0.3355   0.08289   0.08082  -0.0140   1.0000   0.0100
  -6.750  -0.3277   0.08004   0.07800  -0.0157   1.0000   0.0101
  -6.500  -0.3186   0.07715   0.07513  -0.0174   1.0000   0.0105
  -6.250  -0.3082   0.07422   0.07222  -0.0194   1.0000   0.0107
  -6.000  -0.2967   0.07123   0.06925  -0.0214   1.0000   0.0110
  -5.750  -0.2818   0.06804   0.06607  -0.0240   0.9996   0.0117
  -5.500  -0.2268   0.06315   0.06106  -0.0369   0.9854   0.0127
  -5.250  -0.1756   0.05826   0.05603  -0.0472   0.9651   0.0128
  -5.000  -0.1362   0.05229   0.05000  -0.0546   0.9304   0.0130
  -4.750  -0.1014   0.04849   0.04594  -0.0595   0.8656   0.0134
  -4.500  -0.0802   0.04597   0.04314  -0.0606   0.8227   0.0137
  -4.250  -0.0575   0.04344   0.04041  -0.0618   0.7977   0.0141
  -4.000  -0.0331   0.04084   0.03762  -0.0630   0.7796   0.0147
  -3.750  -0.0070   0.03826   0.03486  -0.0641   0.7647   0.0154
  -3.250   0.0581   0.03369   0.02974  -0.0653   0.7407   0.0168
  -3.000   0.0829   0.03012   0.02593  -0.0656   0.7299   0.0171
  -2.750   0.1031   0.02773   0.02345  -0.0660   0.7189   0.0177
  -2.500   0.1276   0.02599   0.02155  -0.0659   0.7084   0.0187
  -2.250   0.1552   0.02423   0.01958  -0.0656   0.6981   0.0207
  -2.000   0.1885   0.02384   0.01877  -0.0642   0.6897   0.0223
  -1.750   0.2115   0.02029   0.01504  -0.0643   0.6821   0.0233
  -1.500   0.2369   0.01891   0.01353  -0.0641   0.6751   0.0242
  -1.250   0.2636   0.01770   0.01215  -0.0637   0.6677   0.0256
  -1.000   0.2916   0.01675   0.01096  -0.0630   0.6612   0.0283
  -0.750   0.3208   0.01674   0.01066  -0.0621   0.6535   0.0298
   0.500   0.4551   0.01059   0.00365  -0.0591   0.6163   0.0309
   0.750   0.4814   0.01004   0.00313  -0.0586   0.6088   0.0340
   1.000   0.5077   0.00966   0.00270  -0.0580   0.6013   0.0357
   1.250   0.5341   0.00937   0.00238  -0.0575   0.5928   0.0377
   1.500   0.5605   0.00913   0.00211  -0.0570   0.5840   0.0412
   1.750   0.5869   0.00897   0.00190  -0.0565   0.5735   0.0447
   2.000   0.6135   0.00890   0.00178  -0.0561   0.5613   0.0499
   2.250   0.6403   0.00884   0.00175  -0.0557   0.5490   0.0654
   2.500   0.6843   0.00699   0.00185  -0.0598   0.5334   1.0000
   2.750   0.7103   0.00709   0.00186  -0.0592   0.5182   1.0000
   3.000   0.7362   0.00721   0.00189  -0.0587   0.5029   1.0000
   3.250   0.7621   0.00733   0.00195  -0.0582   0.4853   1.0000
   3.500   0.7878   0.00748   0.00202  -0.0577   0.4642   1.0000
   3.750   0.8130   0.00768   0.00211  -0.0572   0.4395   1.0000
   4.000   0.8379   0.00793   0.00223  -0.0566   0.4104   1.0000
   4.250   0.8623   0.00824   0.00241  -0.0559   0.3780   1.0000
   4.500   0.8864   0.00860   0.00262  -0.0553   0.3468   1.0000
   4.750   0.9107   0.00896   0.00284  -0.0547   0.3193   1.0000
   5.000   0.9351   0.00931   0.00309  -0.0541   0.2920   1.0000
   5.250   0.9590   0.00972   0.00335  -0.0535   0.2599   1.0000
   5.500   0.9823   0.01020   0.00367  -0.0528   0.2216   1.0000
   5.750   1.0052   0.01073   0.00403  -0.0521   0.1910   1.0000
   6.000   1.0284   0.01121   0.00441  -0.0514   0.1718   1.0000
   6.250   1.0520   0.01164   0.00478  -0.0508   0.1571   1.0000
   6.500   1.0755   0.01207   0.00518  -0.0502   0.1446   1.0000
   6.750   1.0995   0.01244   0.00553  -0.0496   0.1342   1.0000
   7.000   1.1235   0.01280   0.00590  -0.0490   0.1253   1.0000
   7.250   1.1466   0.01326   0.00633  -0.0483   0.1172   1.0000
   7.500   1.1705   0.01360   0.00673  -0.0478   0.1111   1.0000
   7.750   1.1927   0.01414   0.00724  -0.0470   0.1048   1.0000
   8.000   1.2165   0.01447   0.00765  -0.0464   0.1007   1.0000
   8.250   1.2390   0.01494   0.00813  -0.0457   0.0958   1.0000
   8.500   1.2604   0.01551   0.00876  -0.0448   0.0910   1.0000
   8.750   1.2837   0.01586   0.00917  -0.0442   0.0862   1.0000
   9.000   1.3032   0.01659   0.00987  -0.0432   0.0794   1.0000
   9.250   1.3273   0.01681   0.01021  -0.0427   0.0756   1.0000
   9.500   1.3491   0.01727   0.01069  -0.0420   0.0703   1.0000
   9.750   1.3698   0.01781   0.01129  -0.0412   0.0657   1.0000
  10.000   1.3922   0.01816   0.01171  -0.0405   0.0614   1.0000
  10.250   1.4114   0.01880   0.01236  -0.0395   0.0560   1.0000
  10.500   1.4336   0.01913   0.01279  -0.0389   0.0517   1.0000
  10.750   1.4527   0.01973   0.01338  -0.0379   0.0450   1.0000
  11.000   1.4703   0.02044   0.01408  -0.0368   0.0356   1.0000
  11.250   1.4811   0.02175   0.01528  -0.0348   0.0203   1.0000
  11.500   1.4888   0.02324   0.01678  -0.0324   0.0145   1.0000
  11.750   1.4967   0.02449   0.01814  -0.0300   0.0128   1.0000
  12.000   1.4962   0.02604   0.01980  -0.0264   0.0114   1.0000
  12.250   1.4946   0.02770   0.02161  -0.0233   0.0106   1.0000
  12.500   1.4967   0.02922   0.02329  -0.0210   0.0102   1.0000
  12.750   1.4972   0.03105   0.02526  -0.0192   0.0096   1.0000
  13.000   1.4956   0.03327   0.02762  -0.0179   0.0091   1.0000
  13.250   1.4932   0.03584   0.03033  -0.0172   0.0087   1.0000
  13.500   1.4876   0.03896   0.03360  -0.0169   0.0084   1.0000
  13.750   1.4807   0.04247   0.03724  -0.0170   0.0083   1.0000
  14.000   1.4686   0.04681   0.04173  -0.0177   0.0080   1.0000
  14.250   1.4545   0.05163   0.04670  -0.0188   0.0078   1.0000
  14.500   1.4421   0.05645   0.05167  -0.0200   0.0077   1.0000
  14.750   1.4261   0.06195   0.05732  -0.0218   0.0076   1.0000
  15.000   1.4120   0.06744   0.06296  -0.0238   0.0076   1.0000
  15.250   1.3947   0.07366   0.06934  -0.0262   0.0075   1.0000
  15.500   1.3814   0.07969   0.07550  -0.0289   0.0074   1.0000
  15.750   1.3681   0.08592   0.08187  -0.0317   0.0074   1.0000
  16.000   1.3569   0.09212   0.08821  -0.0347   0.0074   1.0000
  16.250   1.3441   0.09877   0.09500  -0.0380   0.0073   1.0000
  16.500   1.3316   0.10553   0.10189  -0.0414   0.0073   1.0000
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