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GOE 240 (KOLLER) AIRFOIL (goe240-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 240 (KOLLER) AIRFOIL (goe240-il)
Reynolds number: 100,000
Max Cl/Cd: 62.24 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe240-il-100000-n5.txt
Download as CSV file: xf-goe240-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 240 (KOLLER) AIRFOIL                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3053   0.09606   0.09148  -0.0265   1.0000   0.0398
  -7.250  -0.3126   0.09474   0.09030  -0.0264   1.0000   0.0406
  -7.000  -0.3181   0.09342   0.08908  -0.0276   1.0000   0.0411
  -6.750  -0.3228   0.09199   0.08773  -0.0288   1.0000   0.0413
  -6.500  -0.3006   0.08684   0.08257  -0.0351   0.9944   0.0421
  -6.250  -0.2882   0.08294   0.07868  -0.0321   0.9908   0.0449
  -6.000  -0.2576   0.07879   0.07448  -0.0400   0.9835   0.0496
  -5.750  -0.2035   0.07358   0.06907  -0.0593   0.9729   0.0523
  -5.500  -0.1918   0.06927   0.06482  -0.0569   0.9675   0.0539
  -5.250  -0.1630   0.06563   0.06113  -0.0610   0.9610   0.0584
  -5.000  -0.1149   0.06065   0.05592  -0.0733   0.9524   0.0645
  -4.750  -0.0919   0.05716   0.05240  -0.0748   0.9440   0.0670
  -4.500  -0.0560   0.05344   0.04854  -0.0802   0.9369   0.0710
  -4.250  -0.0043   0.04974   0.04431  -0.0902   0.9264   0.0764
  -3.750   0.0503   0.04122   0.03558  -0.0941   0.9117   0.0599
  -3.500   0.0983   0.03549   0.02909  -0.0997   0.9065   0.0518
  -3.250   0.1281   0.03265   0.02591  -0.1011   0.8977   0.0518
  -3.000   0.1612   0.03000   0.02303  -0.1030   0.8923   0.0510
  -2.750   0.1914   0.02772   0.02042  -0.1040   0.8841   0.0505
  -2.500   0.2262   0.02551   0.01779  -0.1055   0.8787   0.0505
  -2.250   0.2576   0.02382   0.01561  -0.1061   0.8708   0.0524
  -2.000   0.2910   0.02225   0.01371  -0.1070   0.8651   0.0526
  -1.750   0.3211   0.02102   0.01217  -0.1073   0.8571   0.0524
  -1.500   0.3536   0.01985   0.01074  -0.1079   0.8510   0.0526
  -1.250   0.3828   0.01897   0.00970  -0.1080   0.8425   0.0531
  -0.750   0.4423   0.01759   0.00812  -0.1081   0.8264   0.0551
  -0.500   0.4711   0.01708   0.00753  -0.1079   0.8162   0.0570
  -0.250   0.4997   0.01671   0.00704  -0.1076   0.8046   0.0615
   0.000   0.5277   0.01631   0.00659  -0.1072   0.7922   0.0651
   0.250   0.5538   0.01604   0.00628  -0.1065   0.7793   0.0683
   0.500   0.5804   0.01585   0.00601  -0.1059   0.7678   0.0735
   0.750   0.6079   0.01566   0.00578  -0.1055   0.7572   0.0835
   1.000   0.6357   0.01548   0.00555  -0.1051   0.7467   0.1070
   1.250   0.6620   0.01518   0.00556  -0.1048   0.7344   0.2045
   1.750   0.7145   0.01378   0.00557  -0.1038   0.7098   1.0000
   2.000   0.7407   0.01391   0.00558  -0.1032   0.6968   1.0000
   2.250   0.7667   0.01403   0.00562  -0.1026   0.6832   1.0000
   2.500   0.7924   0.01416   0.00568  -0.1020   0.6682   1.0000
   2.750   0.8177   0.01428   0.00573  -0.1013   0.6501   1.0000
   3.000   0.8427   0.01439   0.00573  -0.1004   0.6293   1.0000
   3.250   0.8672   0.01452   0.00577  -0.0995   0.6047   1.0000
   3.500   0.8916   0.01469   0.00577  -0.0985   0.5788   1.0000
   3.750   0.9157   0.01493   0.00583  -0.0975   0.5538   1.0000
   4.000   0.9399   0.01523   0.00602  -0.0967   0.5315   1.0000
   4.250   0.9642   0.01555   0.00627  -0.0959   0.5122   1.0000
   4.500   0.9883   0.01591   0.00655  -0.0952   0.4932   1.0000
   4.750   1.0121   0.01626   0.00688  -0.0944   0.4716   1.0000
   5.000   1.0354   0.01664   0.00723  -0.0936   0.4483   1.0000
   5.250   1.0584   0.01703   0.00758  -0.0927   0.4229   1.0000
   5.500   1.0808   0.01746   0.00795  -0.0918   0.3973   1.0000
   5.750   1.1027   0.01794   0.00835  -0.0908   0.3735   1.0000
   6.000   1.1248   0.01844   0.00884  -0.0899   0.3521   1.0000
   6.250   1.1463   0.01900   0.00935  -0.0889   0.3320   1.0000
   6.500   1.1673   0.01959   0.00991  -0.0879   0.3131   1.0000
   6.750   1.1886   0.02017   0.01051  -0.0869   0.2947   1.0000
   7.000   1.2097   0.02076   0.01117  -0.0859   0.2773   1.0000
   7.250   1.2302   0.02138   0.01183  -0.0849   0.2592   1.0000
   7.500   1.2486   0.02212   0.01249  -0.0836   0.2325   1.0000
   7.750   1.2657   0.02295   0.01321  -0.0822   0.2046   1.0000
   8.000   1.2835   0.02375   0.01398  -0.0809   0.1868   1.0000
   8.250   1.3001   0.02463   0.01487  -0.0795   0.1694   1.0000
   8.500   1.3169   0.02549   0.01577  -0.0781   0.1550   1.0000
   8.750   1.3325   0.02642   0.01673  -0.0765   0.1383   1.0000
   9.000   1.3468   0.02749   0.01776  -0.0749   0.1071   1.0000
   9.250   1.3505   0.02946   0.01930  -0.0721   0.0574   1.0000
   9.500   1.3568   0.03107   0.02098  -0.0694   0.0447   1.0000
   9.750   1.3636   0.03257   0.02265  -0.0667   0.0331   1.0000
  10.250   1.3730   0.03597   0.02616  -0.0617   0.0235   1.0000
  10.500   1.3755   0.03790   0.02820  -0.0593   0.0218   1.0000
  10.750   1.3758   0.04007   0.03053  -0.0571   0.0208   1.0000
  11.000   1.3732   0.04258   0.03324  -0.0550   0.0200   1.0000
  11.250   1.3709   0.04519   0.03606  -0.0534   0.0196   1.0000
  11.500   1.3674   0.04807   0.03916  -0.0521   0.0192   1.0000
  11.750   1.3627   0.05123   0.04254  -0.0511   0.0189   1.0000
  12.000   1.3568   0.05467   0.04619  -0.0504   0.0185   1.0000
  12.250   1.3501   0.05835   0.05008  -0.0501   0.0180   1.0000
  12.500   1.3429   0.06226   0.05417  -0.0500   0.0176   1.0000
  12.750   1.3352   0.06639   0.05852  -0.0502   0.0172   1.0000
  13.000   1.3274   0.07068   0.06300  -0.0507   0.0168   1.0000
  13.250   1.3194   0.07513   0.06761  -0.0514   0.0164   1.0000
  13.500   1.3118   0.07966   0.07230  -0.0522   0.0161   1.0000
  13.750   1.3049   0.08417   0.07697  -0.0531   0.0158   1.0000
  14.000   1.2989   0.08859   0.08154  -0.0539   0.0156   1.0000
  14.250   1.2940   0.09291   0.08600  -0.0547   0.0154   1.0000
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