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GOE 264 AIRFOIL (goe264-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 264 AIRFOIL (goe264-il)
Reynolds number: 100,000
Max Cl/Cd: 60.82 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe264-il-100000-n5.txt
Download as CSV file: xf-goe264-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 264 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3018   0.10233   0.09771  -0.0260   1.0000   0.0414
  -7.500  -0.3027   0.10076   0.09623  -0.0276   1.0000   0.0416
  -7.250  -0.3017   0.09880   0.09433  -0.0292   1.0000   0.0418
  -7.000  -0.2995   0.09658   0.09218  -0.0307   1.0000   0.0419
  -6.750  -0.2960   0.09412   0.08976  -0.0321   1.0000   0.0419
  -6.500  -0.2913   0.09144   0.08711  -0.0333   1.0000   0.0420
  -6.250  -0.2855   0.08860   0.08429  -0.0345   1.0000   0.0420
  -5.750  -0.2566   0.07896   0.07469  -0.0335   0.9920   0.0462
  -5.500  -0.2193   0.07478   0.07042  -0.0424   0.9857   0.0514
  -5.250  -0.1561   0.07037   0.06574  -0.0605   0.9776   0.0539
  -4.750  -0.1061   0.06078   0.05613  -0.0661   0.9659   0.0586
  -4.500  -0.0670   0.05683   0.05204  -0.0727   0.9584   0.0625
  -4.000   0.0164   0.04926   0.04415  -0.0860   0.9430   0.0749
  -3.750   0.0684   0.04419   0.03872  -0.0944   0.9369   0.0647
  -3.500   0.1181   0.04061   0.03469  -0.1011   0.9266   0.0678
  -3.250   0.1476   0.03753   0.03152  -0.1031   0.9162   0.0649
  -3.000   0.1873   0.03437   0.02808  -0.1068   0.9067   0.0631
  -2.750   0.2245   0.03162   0.02503  -0.1096   0.8944   0.0627
  -2.500   0.2628   0.02916   0.02214  -0.1121   0.8815   0.0665
  -2.250   0.2972   0.02694   0.01960  -0.1138   0.8678   0.0658
  -2.000   0.3313   0.02486   0.01716  -0.1151   0.8534   0.0652
  -1.750   0.3645   0.02298   0.01490  -0.1161   0.8381   0.0652
  -1.500   0.3967   0.02133   0.01282  -0.1166   0.8219   0.0658
  -1.250   0.4272   0.01999   0.01107  -0.1168   0.8037   0.0670
  -1.000   0.4566   0.01898   0.00970  -0.1167   0.7843   0.0685
  -0.750   0.4839   0.01851   0.00916  -0.1165   0.7639   0.0724
  -0.500   0.5116   0.01806   0.00855  -0.1162   0.7422   0.0765
  -0.250   0.5395   0.01743   0.00767  -0.1158   0.7209   0.0784
   0.000   0.5671   0.01691   0.00693  -0.1153   0.6998   0.0807
   0.250   0.5940   0.01653   0.00639  -0.1148   0.6798   0.0834
   0.500   0.6209   0.01631   0.00608  -0.1144   0.6613   0.0873
   0.750   0.6473   0.01617   0.00580  -0.1139   0.6439   0.0939
   1.000   0.6739   0.01614   0.00571  -0.1134   0.6272   0.1038
   1.250   0.7009   0.01609   0.00555  -0.1130   0.6116   0.1141
   1.500   0.7280   0.01607   0.00546  -0.1128   0.5966   0.1305
   1.750   0.7553   0.01609   0.00546  -0.1126   0.5820   0.1594
   2.000   0.7826   0.01612   0.00554  -0.1125   0.5679   0.2015
   2.250   0.8100   0.01611   0.00564  -0.1126   0.5542   0.2682
   2.500   0.8292   0.01493   0.00566  -0.1105   0.5418   1.0000
   2.750   0.8562   0.01519   0.00577  -0.1103   0.5286   1.0000
   3.000   0.8831   0.01547   0.00594  -0.1101   0.5160   1.0000
   3.250   0.9099   0.01575   0.00615  -0.1099   0.5039   1.0000
   3.500   0.9365   0.01605   0.00637  -0.1097   0.4926   1.0000
   3.750   0.9630   0.01637   0.00660  -0.1094   0.4823   1.0000
   4.000   0.9897   0.01668   0.00694  -0.1092   0.4718   1.0000
   4.250   1.0162   0.01702   0.00726  -0.1090   0.4623   1.0000
   4.500   1.0424   0.01738   0.00759  -0.1088   0.4535   1.0000
   4.750   1.0688   0.01774   0.00799  -0.1086   0.4443   1.0000
   5.000   1.0950   0.01814   0.00841  -0.1083   0.4369   1.0000
   5.250   1.1213   0.01853   0.00890  -0.1081   0.4289   1.0000
   5.500   1.1473   0.01896   0.00934  -0.1079   0.4225   1.0000
   5.750   1.1733   0.01938   0.00990  -0.1076   0.4145   1.0000
   6.000   1.1990   0.01983   0.01042  -0.1073   0.4077   1.0000
   6.250   1.2244   0.02026   0.01103  -0.1070   0.3992   1.0000
   6.500   1.2497   0.02071   0.01158  -0.1066   0.3918   1.0000
   6.750   1.2728   0.02103   0.01202  -0.1058   0.3756   1.0000
   7.000   1.2925   0.02125   0.01230  -0.1045   0.3447   1.0000
   7.250   1.3124   0.02165   0.01272  -0.1033   0.3117   1.0000
   7.500   1.3315   0.02226   0.01332  -0.1021   0.2701   1.0000
   7.750   1.3324   0.02499   0.01491  -0.0991   0.1112   1.0000
   8.000   1.3344   0.02799   0.01741  -0.0962   0.0468   1.0000
   8.500   1.3540   0.03142   0.02118  -0.0915   0.0328   1.0000
   8.750   1.3599   0.03318   0.02310  -0.0889   0.0294   1.0000
   9.000   1.3619   0.03504   0.02518  -0.0858   0.0273   1.0000
   9.250   1.3615   0.03680   0.02716  -0.0824   0.0260   1.0000
   9.500   1.3593   0.03889   0.02945  -0.0793   0.0250   1.0000
   9.750   1.3565   0.04124   0.03197  -0.0767   0.0242   1.0000
  10.000   1.3537   0.04377   0.03466  -0.0745   0.0233   1.0000
  10.250   1.3519   0.04642   0.03744  -0.0727   0.0223   1.0000
  10.500   1.3509   0.04913   0.04026  -0.0713   0.0213   1.0000
  10.750   1.3501   0.05194   0.04315  -0.0700   0.0202   1.0000
  11.000   1.3498   0.05481   0.04607  -0.0685   0.0192   1.0000
  11.250   1.3554   0.05742   0.04870  -0.0660   0.0184   1.0000
  11.500   1.3649   0.05972   0.05112  -0.0643   0.0180   1.0000
  11.750   1.3746   0.06214   0.05374  -0.0628   0.0176   1.0000
  12.000   1.3833   0.06483   0.05663  -0.0613   0.0173   1.0000
  12.250   1.3876   0.06791   0.06002  -0.0602   0.0169   1.0000
  12.500   1.3885   0.07129   0.06366  -0.0595   0.0165   1.0000
  12.750   1.3863   0.07498   0.06761  -0.0591   0.0160   1.0000
  13.000   1.3817   0.07899   0.07188  -0.0590   0.0156   1.0000
  13.250   1.3750   0.08334   0.07649  -0.0593   0.0152   1.0000
  13.500   1.3664   0.08806   0.08146  -0.0601   0.0150   1.0000
  13.750   1.3558   0.09320   0.08684  -0.0613   0.0148   1.0000
  14.000   1.3436   0.09870   0.09260  -0.0630   0.0148   1.0000
  14.250   1.3301   0.10465   0.09879  -0.0653   0.0148   1.0000
  14.500   1.3157   0.11105   0.10543  -0.0682   0.0148   1.0000
  14.750   1.3005   0.11792   0.11253  -0.0717   0.0148   1.0000
  15.000   1.2848   0.12529   0.12012  -0.0759   0.0149   1.0000
  15.250   1.2689   0.13322   0.12824  -0.0807   0.0150   1.0000
  15.500   1.2525   0.14179   0.13701  -0.0863   0.0151   1.0000
  15.750   1.2359   0.15110   0.14648  -0.0925   0.0153   1.0000
  16.000   1.2190   0.16130   0.15683  -0.0995   0.0155   1.0000
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