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GOE 370 AIRFOIL (goe370-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 370 AIRFOIL (goe370-il)
Reynolds number: 500,000
Max Cl/Cd: 128.11 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe370-il-500000.txt
Download as CSV file: xf-goe370-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 370 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3080   0.09768   0.09551  -0.0281   1.0000   0.0130
  -7.750  -0.3108   0.09595   0.09383  -0.0273   1.0000   0.0131
  -7.500  -0.3203   0.09490   0.09285  -0.0251   1.0000   0.0131
  -7.250  -0.3102   0.09194   0.08991  -0.0283   0.9976   0.0131
  -7.000  -0.2809   0.08719   0.08515  -0.0367   0.9930   0.0132
  -6.750  -0.2532   0.08255   0.08050  -0.0442   0.9876   0.0133
  -6.500  -0.2222   0.07768   0.07560  -0.0522   0.9834   0.0133
  -6.250  -0.2110   0.07207   0.07001  -0.0534   0.9770   0.0142
  -6.000  -0.1823   0.06830   0.06622  -0.0592   0.9716   0.0149
  -5.750  -0.1524   0.06450   0.06238  -0.0655   0.9634   0.0163
  -5.500  -0.0998   0.06021   0.05801  -0.0782   0.9568   0.0195
  -5.250  -0.0574   0.05633   0.05402  -0.0865   0.9464   0.0199
  -5.000  -0.0196   0.05182   0.04942  -0.0935   0.9354   0.0199
  -4.750   0.0158   0.04745   0.04493  -0.0994   0.9227   0.0200
  -4.500   0.0431   0.04040   0.03772  -0.1054   0.9072   0.0209
  -4.250   0.0671   0.03792   0.03512  -0.1071   0.8936   0.0218
  -4.000   0.0920   0.03591   0.03299  -0.1084   0.8812   0.0233
  -3.750   0.1270   0.03402   0.03091  -0.1107   0.8704   0.0295
  -3.000   0.2097   0.01972   0.01561  -0.1153   0.8436   0.0264
  -2.750   0.2356   0.01430   0.00938  -0.1150   0.8361   0.0270
  -2.500   0.2628   0.01398   0.00882  -0.1147   0.8291   0.0298
  -2.250   0.2876   0.01147   0.00578  -0.1142   0.8221   0.0334
  -2.000   0.3141   0.01082   0.00495  -0.1139   0.8156   0.0359
  -1.750   0.3407   0.01040   0.00440  -0.1135   0.8088   0.0394
  -1.500   0.3675   0.00997   0.00382  -0.1132   0.8029   0.0413
  -1.250   0.3940   0.00955   0.00329  -0.1128   0.7964   0.0421
  -1.000   0.4208   0.00925   0.00288  -0.1124   0.7907   0.0426
  -0.750   0.4467   0.00877   0.00234  -0.1119   0.7839   0.0444
  -0.500   0.4730   0.00848   0.00199  -0.1115   0.7778   0.0464
  -0.250   0.4994   0.00830   0.00180  -0.1111   0.7712   0.0506
   0.000   0.5260   0.00819   0.00165  -0.1107   0.7650   0.0573
   0.250   0.5521   0.00802   0.00160  -0.1103   0.7576   0.0909
   0.500   0.5784   0.00802   0.00163  -0.1099   0.7492   0.1295
   0.750   0.6044   0.00800   0.00163  -0.1094   0.7387   0.1459
   1.000   0.6303   0.00800   0.00162  -0.1090   0.7281   0.1623
   1.250   0.6562   0.00797   0.00160  -0.1085   0.7180   0.1758
   1.500   0.6822   0.00795   0.00160  -0.1081   0.7084   0.1908
   1.750   0.7081   0.00787   0.00165  -0.1077   0.6987   0.2217
   2.000   0.7316   0.00744   0.00180  -0.1071   0.6894   0.4774
   2.250   0.7809   0.00652   0.00185  -0.1120   0.6790   1.0000
   2.500   0.8062   0.00660   0.00189  -0.1114   0.6675   1.0000
   2.750   0.8314   0.00668   0.00195  -0.1108   0.6556   1.0000
   3.000   0.8566   0.00678   0.00205  -0.1102   0.6433   1.0000
   3.250   0.8814   0.00688   0.00214  -0.1095   0.6284   1.0000
   3.500   0.9039   0.00706   0.00219  -0.1083   0.5959   1.0000
   3.750   0.9256   0.00735   0.00231  -0.1070   0.5594   1.0000
   4.000   0.9474   0.00768   0.00249  -0.1058   0.5261   1.0000
   4.250   0.9694   0.00803   0.00274  -0.1046   0.4904   1.0000
   4.500   0.9851   0.00883   0.00306  -0.1024   0.3803   1.0000
   4.750   0.9776   0.01210   0.00453  -0.0969   0.0538   1.0000
   5.000   0.9968   0.01292   0.00527  -0.0952   0.0255   1.0000
   5.250   1.0158   0.01377   0.00627  -0.0934   0.0210   1.0000
   5.500   1.0375   0.01427   0.00682  -0.0923   0.0190   1.0000
   5.750   1.0576   0.01492   0.00754  -0.0908   0.0171   1.0000
   6.000   1.0761   0.01572   0.00843  -0.0891   0.0157   1.0000
   6.250   1.0922   0.01673   0.00952  -0.0870   0.0146   1.0000
   6.500   1.1034   0.01831   0.01119  -0.0841   0.0137   1.0000
   6.750   1.1171   0.01999   0.01294  -0.0816   0.0135   1.0000
   7.000   1.1364   0.02344   0.01645  -0.0802   0.0128   1.0000
   7.250   1.1221   0.01194   0.00539  -0.0742   0.0120   1.0000
   7.500   1.1454   0.01404   0.00761  -0.0733   0.0117   1.0000
   7.750   1.1698   0.01695   0.01074  -0.0726   0.0116   1.0000
  10.750   1.2370   0.07175   0.06818  -0.0448   0.0127   1.0000
  11.000   1.2189   0.07463   0.07121  -0.0419   0.0127   1.0000
  11.250   1.2004   0.07804   0.07477  -0.0402   0.0127   1.0000
  11.500   1.1814   0.08172   0.07860  -0.0394   0.0127   1.0000
  11.750   1.1630   0.08631   0.08332  -0.0397   0.0127   1.0000
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