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GOE 596 AIRFOIL (goe596-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 596 AIRFOIL (goe596-il)
Reynolds number: 500,000
Max Cl/Cd: 97.22 at α=4°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe596-il-500000-n5.txt
Download as CSV file: xf-goe596-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 596 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3637   0.08827   0.08592  -0.0359   1.0000   0.0171
  -9.000  -0.3642   0.08539   0.08306  -0.0364   1.0000   0.0173
  -8.750  -0.3671   0.08257   0.08028  -0.0366   1.0000   0.0176
  -8.500  -0.3582   0.07796   0.07568  -0.0415   0.9900   0.0181
  -8.250  -0.3513   0.07210   0.06982  -0.0489   0.9762   0.0187
  -8.000  -0.3415   0.05790   0.05550  -0.0699   0.9595   0.0201
  -7.750  -0.3160   0.05403   0.05155  -0.0761   0.9493   0.0204
  -7.500  -0.2919   0.04945   0.04685  -0.0823   0.9368   0.0208
  -7.250  -0.2717   0.04432   0.04154  -0.0872   0.9218   0.0213
  -7.000  -0.2561   0.03907   0.03602  -0.0902   0.9059   0.0221
  -6.750  -0.2668   0.02474   0.02050  -0.0908   0.8872   0.0240
  -6.500  -0.2504   0.02181   0.01712  -0.0900   0.8753   0.0247
  -6.250  -0.2275   0.02086   0.01600  -0.0896   0.8642   0.0250
  -6.000  -0.2042   0.01997   0.01494  -0.0891   0.8536   0.0253
  -5.750  -0.1813   0.01884   0.01360  -0.0884   0.8430   0.0256
  -5.500  -0.1578   0.01775   0.01230  -0.0878   0.8329   0.0259
  -5.250  -0.1337   0.01685   0.01118  -0.0872   0.8220   0.0263
  -5.000  -0.1094   0.01594   0.01008  -0.0866   0.8101   0.0267
  -4.750  -0.0847   0.01513   0.00907  -0.0860   0.7980   0.0270
  -4.500  -0.0595   0.01450   0.00827  -0.0854   0.7852   0.0276
  -4.250  -0.0342   0.01391   0.00750  -0.0848   0.7717   0.0282
  -4.000  -0.0089   0.01331   0.00674  -0.0842   0.7562   0.0286
  -3.750   0.0165   0.01281   0.00608  -0.0836   0.7377   0.0289
  -3.500   0.0417   0.01241   0.00552  -0.0829   0.7160   0.0292
  -3.250   0.0668   0.01210   0.00506  -0.0823   0.6938   0.0295
  -3.000   0.0919   0.01183   0.00464  -0.0816   0.6726   0.0297
  -2.750   0.1164   0.01142   0.00409  -0.0809   0.6525   0.0300
  -2.500   0.1409   0.01108   0.00363  -0.0801   0.6336   0.0306
  -2.250   0.1661   0.01086   0.00332  -0.0795   0.6168   0.0311
  -2.000   0.1917   0.01072   0.00311  -0.0790   0.6030   0.0317
  -1.750   0.2180   0.01057   0.00292  -0.0786   0.5929   0.0326
  -1.500   0.2441   0.01043   0.00274  -0.0782   0.5846   0.0333
  -1.250   0.2706   0.01027   0.00254  -0.0779   0.5770   0.0340
  -1.000   0.2969   0.01015   0.00238  -0.0774   0.5697   0.0347
  -0.750   0.3236   0.01003   0.00224  -0.0771   0.5626   0.0355
  -0.500   0.3502   0.00996   0.00212  -0.0768   0.5559   0.0362
  -0.250   0.3770   0.00987   0.00201  -0.0765   0.5502   0.0369
   0.000   0.4037   0.00976   0.00189  -0.0761   0.5439   0.0387
   0.250   0.4302   0.00973   0.00183  -0.0758   0.5378   0.0409
   0.500   0.4573   0.00968   0.00179  -0.0756   0.5316   0.0440
   0.750   0.4840   0.00965   0.00176  -0.0752   0.5255   0.0493
   1.000   0.5106   0.00960   0.00175  -0.0749   0.5203   0.0652
   1.250   0.5356   0.00919   0.00179  -0.0745   0.5146   0.2315
   1.500   0.5572   0.00851   0.00188  -0.0737   0.5087   0.5178
   2.000   0.6527   0.00763   0.00209  -0.0822   0.4909   1.0000
   2.250   0.6779   0.00771   0.00213  -0.0816   0.4839   1.0000
   2.500   0.7025   0.00782   0.00219  -0.0808   0.4756   1.0000
   2.750   0.7273   0.00792   0.00226  -0.0801   0.4654   1.0000
   3.000   0.7519   0.00804   0.00233  -0.0794   0.4563   1.0000
   3.250   0.7766   0.00816   0.00241  -0.0787   0.4460   1.0000
   3.500   0.8008   0.00831   0.00251  -0.0780   0.4315   1.0000
   3.750   0.8244   0.00851   0.00261  -0.0771   0.4117   1.0000
   4.000   0.8478   0.00872   0.00273  -0.0762   0.3908   1.0000
   4.250   0.8711   0.00896   0.00288  -0.0753   0.3714   1.0000
   4.500   0.8940   0.00924   0.00306  -0.0744   0.3516   1.0000
   4.750   0.9175   0.00949   0.00324  -0.0736   0.3372   1.0000
   5.000   0.9411   0.00974   0.00344  -0.0728   0.3235   1.0000
   5.500   0.9874   0.01031   0.00388  -0.0711   0.2908   1.0000
   5.750   1.0106   0.01060   0.00412  -0.0703   0.2742   1.0000
   6.000   1.0333   0.01092   0.00438  -0.0694   0.2544   1.0000
   6.250   1.0540   0.01140   0.00470  -0.0683   0.2216   1.0000
   6.500   1.0720   0.01209   0.00515  -0.0667   0.1795   1.0000
   6.750   1.0913   0.01267   0.00560  -0.0654   0.1539   1.0000
   7.000   1.1100   0.01328   0.00608  -0.0640   0.1252   1.0000
   7.250   1.1191   0.01460   0.00697  -0.0612   0.0581   1.0000
   7.500   1.1382   0.01513   0.00747  -0.0598   0.0491   1.0000
   7.750   1.1587   0.01553   0.00790  -0.0587   0.0456   1.0000
   8.000   1.1782   0.01600   0.00838  -0.0573   0.0425   1.0000
   8.250   1.1963   0.01652   0.00891  -0.0558   0.0395   1.0000
   8.500   1.2159   0.01692   0.00937  -0.0546   0.0382   1.0000
   8.750   1.2344   0.01737   0.00986  -0.0531   0.0366   1.0000
   9.000   1.2513   0.01785   0.01038  -0.0515   0.0351   1.0000
   9.250   1.2653   0.01840   0.01095  -0.0493   0.0336   1.0000
   9.500   1.2768   0.01905   0.01164  -0.0468   0.0320   1.0000
   9.750   1.2909   0.01957   0.01222  -0.0447   0.0311   1.0000
  10.000   1.3051   0.02011   0.01283  -0.0428   0.0301   1.0000
  10.250   1.3186   0.02070   0.01347  -0.0409   0.0289   1.0000
  10.500   1.3310   0.02138   0.01420  -0.0389   0.0279   1.0000
  10.750   1.3417   0.02217   0.01503  -0.0368   0.0267   1.0000
  11.000   1.3494   0.02318   0.01607  -0.0345   0.0255   1.0000
  11.250   1.3620   0.02393   0.01691  -0.0329   0.0247   1.0000
  11.500   1.3731   0.02481   0.01787  -0.0313   0.0238   1.0000
  11.750   1.3833   0.02579   0.01892  -0.0297   0.0228   1.0000
  12.000   1.3934   0.02681   0.01999  -0.0282   0.0217   1.0000
  12.250   1.4012   0.02807   0.02128  -0.0268   0.0207   1.0000
  12.500   1.4086   0.02941   0.02270  -0.0254   0.0199   1.0000
  12.750   1.4161   0.03082   0.02421  -0.0242   0.0191   1.0000
  13.000   1.4235   0.03228   0.02575  -0.0231   0.0181   1.0000
  13.250   1.4300   0.03390   0.02742  -0.0222   0.0173   1.0000
  13.500   1.4349   0.03574   0.02932  -0.0214   0.0166   1.0000
  13.750   1.4377   0.03787   0.03152  -0.0207   0.0160   1.0000
  14.000   1.4417   0.03998   0.03373  -0.0202   0.0153   1.0000
  14.250   1.4444   0.04231   0.03616  -0.0198   0.0148   1.0000
  14.500   1.4455   0.04490   0.03885  -0.0196   0.0143   1.0000
  14.750   1.4468   0.04753   0.04156  -0.0196   0.0138   1.0000
  15.000   1.4472   0.05034   0.04444  -0.0197   0.0132   1.0000
  15.250   1.4442   0.05365   0.04784  -0.0200   0.0129   1.0000
  15.500   1.4414   0.05700   0.05128  -0.0204   0.0125   1.0000
  15.750   1.4402   0.06024   0.05464  -0.0209   0.0121   1.0000
  16.000   1.4369   0.06382   0.05833  -0.0216   0.0118   1.0000
  16.250   1.4330   0.06754   0.06216  -0.0223   0.0116   1.0000
  16.500   1.4290   0.07138   0.06610  -0.0233   0.0112   1.0000
  16.750   1.4240   0.07546   0.07029  -0.0244   0.0110   1.0000
  17.000   1.4188   0.07964   0.07457  -0.0256   0.0108   1.0000
  17.250   1.4126   0.08409   0.07913  -0.0270   0.0106   1.0000
  17.500   1.4067   0.08861   0.08374  -0.0286   0.0104   1.0000
  17.750   1.3980   0.09366   0.08889  -0.0305   0.0102   1.0000
  18.000   1.3898   0.09873   0.09406  -0.0324   0.0100   1.0000
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