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GOE 394 AIRFOIL (goe394-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 394 AIRFOIL (goe394-il)
Reynolds number: 1,000,000
Max Cl/Cd: 112.61 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe394-il-1000000-n5.txt
Download as CSV file: xf-goe394-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 394 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4031   0.12221   0.11972  -0.0026   0.7458   0.0052
 -10.250  -0.3974   0.11859   0.11609  -0.0042   0.7427   0.0054
  -9.750  -0.3911   0.10982   0.10730  -0.0079   0.7378   0.0061
  -7.750  -0.3170   0.01748   0.01343  -0.1106   0.7217   0.0163
  -7.500  -0.2893   0.01737   0.01335  -0.1105   0.7203   0.0169
  -7.250  -0.2614   0.01773   0.01377  -0.1102   0.7188   0.0174
  -7.000  -0.2336   0.01801   0.01409  -0.1099   0.7174   0.0180
  -6.750  -0.2058   0.01710   0.01306  -0.1104   0.7160   0.0188
  -6.500  -0.1780   0.01594   0.01173  -0.1109   0.7143   0.0195
  -6.250  -0.1502   0.01520   0.01084  -0.1112   0.7119   0.0201
  -5.750  -0.0942   0.01431   0.00973  -0.1115   0.7064   0.0210
  -5.500  -0.0661   0.01400   0.00935  -0.1115   0.7039   0.0213
  -5.250  -0.0379   0.01369   0.00895  -0.1116   0.7012   0.0214
  -5.000  -0.0100   0.01183   0.00674  -0.1123   0.6988   0.0227
  -4.750   0.0181   0.01138   0.00619  -0.1124   0.6963   0.0232
  -4.500   0.0463   0.01099   0.00569  -0.1124   0.6941   0.0236
  -4.250   0.0746   0.01067   0.00531  -0.1125   0.6923   0.0242
  -4.000   0.1030   0.01033   0.00491  -0.1125   0.6902   0.0247
  -3.750   0.1314   0.00996   0.00445  -0.1125   0.6880   0.0251
  -3.500   0.1598   0.00963   0.00403  -0.1125   0.6858   0.0255
  -3.250   0.1882   0.00932   0.00364  -0.1125   0.6834   0.0259
  -3.000   0.2166   0.00905   0.00329  -0.1125   0.6808   0.0261
  -2.750   0.2450   0.00879   0.00296  -0.1125   0.6781   0.0264
  -2.500   0.2735   0.00855   0.00267  -0.1124   0.6755   0.0266
  -2.250   0.3020   0.00833   0.00241  -0.1124   0.6722   0.0269
  -2.000   0.3304   0.00814   0.00217  -0.1124   0.6685   0.0271
  -1.750   0.3588   0.00799   0.00196  -0.1123   0.6649   0.0274
  -1.500   0.3873   0.00785   0.00181  -0.1123   0.6616   0.0279
  -1.250   0.4158   0.00770   0.00165  -0.1123   0.6573   0.0282
  -1.000   0.4442   0.00759   0.00150  -0.1122   0.6525   0.0285
  -0.750   0.4726   0.00750   0.00139  -0.1121   0.6476   0.0288
  -0.500   0.5010   0.00741   0.00129  -0.1121   0.6406   0.0291
  -0.250   0.5293   0.00733   0.00117  -0.1120   0.6325   0.0302
   0.000   0.5576   0.00726   0.00107  -0.1120   0.6198   0.0321
   0.250   0.5855   0.00727   0.00098  -0.1119   0.5914   0.0342
   0.500   0.6124   0.00747   0.00097  -0.1116   0.5421   0.0367
   1.000   0.6670   0.00771   0.00113  -0.1114   0.4901   0.0745
   1.250   0.6945   0.00788   0.00124  -0.1113   0.4705   0.0812
   1.500   0.7220   0.00802   0.00132  -0.1112   0.4527   0.0839
   1.750   0.7495   0.00815   0.00141  -0.1111   0.4371   0.0869
   2.000   0.7770   0.00828   0.00151  -0.1110   0.4239   0.0906
   2.250   0.8046   0.00838   0.00159  -0.1109   0.4138   0.0930
   2.500   0.8322   0.00848   0.00167  -0.1108   0.4028   0.0945
   2.750   0.8597   0.00860   0.00177  -0.1107   0.3924   0.0960
   3.000   0.8871   0.00869   0.00185  -0.1106   0.3836   0.0980
   3.250   0.9146   0.00876   0.00192  -0.1105   0.3750   0.0996
   3.500   0.9419   0.00888   0.00202  -0.1104   0.3643   0.1009
   3.750   0.9693   0.00897   0.00212  -0.1103   0.3551   0.1023
   4.000   0.9965   0.00908   0.00223  -0.1102   0.3456   0.1038
   4.250   1.0234   0.00924   0.00237  -0.1101   0.3323   0.1053
   4.500   1.0502   0.00942   0.00251  -0.1099   0.3179   0.1069
   4.750   1.0769   0.00959   0.00267  -0.1097   0.3054   0.1085
   5.000   1.1033   0.00980   0.00285  -0.1095   0.2893   0.1103
   5.250   1.1295   0.01003   0.00304  -0.1093   0.2714   0.1139
   5.500   1.1538   0.01053   0.00336  -0.1089   0.2313   0.1176
   6.000   1.1972   0.01225   0.00448  -0.1075   0.1114   0.1425
   6.500   1.2458   0.01175   0.00531  -0.1068   0.0906   1.0000
   6.750   1.2707   0.01211   0.00562  -0.1064   0.0799   1.0000
   7.000   1.2946   0.01257   0.00600  -0.1060   0.0636   1.0000
   7.250   1.3165   0.01330   0.00655  -0.1052   0.0373   1.0000
   7.500   1.3389   0.01392   0.00709  -0.1045   0.0232   1.0000
   7.750   1.3617   0.01447   0.00759  -0.1038   0.0160   1.0000
   8.000   1.3849   0.01494   0.00807  -0.1032   0.0127   1.0000
   8.250   1.4081   0.01537   0.00853  -0.1026   0.0112   1.0000
   8.500   1.4305   0.01588   0.00904  -0.1019   0.0098   1.0000
   8.750   1.4528   0.01638   0.00957  -0.1011   0.0089   1.0000
   9.000   1.4750   0.01684   0.01008  -0.1004   0.0083   1.0000
   9.250   1.4966   0.01735   0.01062  -0.0996   0.0076   1.0000
   9.500   1.5172   0.01793   0.01123  -0.0987   0.0070   1.0000
   9.750   1.5366   0.01861   0.01195  -0.0976   0.0063   1.0000
  10.000   1.5567   0.01915   0.01254  -0.0966   0.0060   1.0000
  10.250   1.5758   0.01976   0.01320  -0.0955   0.0057   1.0000
  10.500   1.5940   0.02041   0.01390  -0.0942   0.0054   1.0000
  10.750   1.6110   0.02110   0.01464  -0.0929   0.0051   1.0000
  11.000   1.6264   0.02185   0.01545  -0.0913   0.0049   1.0000
  11.250   1.6377   0.02268   0.01634  -0.0891   0.0046   1.0000
  11.500   1.6460   0.02374   0.01747  -0.0866   0.0044   1.0000
  11.750   1.6552   0.02480   0.01861  -0.0845   0.0043   1.0000
  12.000   1.6649   0.02586   0.01975  -0.0826   0.0042   1.0000
  12.250   1.6739   0.02705   0.02102  -0.0808   0.0041   1.0000
  12.500   1.6821   0.02836   0.02242  -0.0791   0.0040   1.0000
  12.750   1.6900   0.02977   0.02391  -0.0776   0.0038   1.0000
  13.000   1.6971   0.03132   0.02554  -0.0762   0.0037   1.0000
  13.250   1.7035   0.03300   0.02732  -0.0750   0.0036   1.0000
  13.500   1.7096   0.03477   0.02917  -0.0738   0.0035   1.0000
  13.750   1.7147   0.03668   0.03116  -0.0728   0.0034   1.0000
  14.000   1.7188   0.03875   0.03332  -0.0718   0.0033   1.0000
  14.250   1.7208   0.04106   0.03572  -0.0708   0.0032   1.0000
  14.500   1.7213   0.04359   0.03834  -0.0699   0.0031   1.0000
  14.750   1.7199   0.04637   0.04122  -0.0691   0.0030   1.0000
  15.000   1.7158   0.04951   0.04446  -0.0684   0.0030   1.0000
  15.250   1.7093   0.05302   0.04809  -0.0678   0.0029   1.0000
  15.500   1.7001   0.05700   0.05220  -0.0675   0.0028   1.0000
  15.750   1.6915   0.06113   0.05646  -0.0675   0.0028   1.0000
  16.000   1.6851   0.06518   0.06063  -0.0678   0.0028   1.0000
  16.250   1.6782   0.06951   0.06507  -0.0684   0.0028   1.0000
  16.500   1.6695   0.07427   0.06996  -0.0693   0.0027   1.0000
  16.750   1.6604   0.07926   0.07508  -0.0705   0.0027   1.0000
  17.000   1.6498   0.08463   0.08057  -0.0720   0.0027   1.0000
  17.250   1.6382   0.09020   0.08627  -0.0736   0.0027   1.0000
  17.500   1.6252   0.09609   0.09229  -0.0754   0.0027   1.0000
  17.750   1.6115   0.10219   0.09852  -0.0775   0.0027   1.0000
  18.000   1.5969   0.10853   0.10498  -0.0797   0.0026   1.0000
  18.250   1.5818   0.11500   0.11159  -0.0822   0.0026   1.0000
  18.500   1.5670   0.12159   0.11830  -0.0848   0.0026   1.0000
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