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GOE 264 AIRFOIL (goe264-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 264 AIRFOIL (goe264-il)
Reynolds number: 1,000,000
Max Cl/Cd: 121.8 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe264-il-1000000-n5.txt
Download as CSV file: xf-goe264-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3396   0.09584   0.09431  -0.0234   0.9834   0.0050
  -8.500  -0.3328   0.09164   0.09009  -0.0263   0.9683   0.0053
  -8.000  -0.3386   0.07665   0.07505  -0.0389   0.9365   0.0066
  -7.750  -0.3230   0.07382   0.07219  -0.0421   0.9224   0.0069
  -7.500  -0.3057   0.07057   0.06888  -0.0461   0.9077   0.0072
  -7.000  -0.2217   0.01374   0.00980  -0.1105   0.8892   0.0113
  -6.750  -0.1938   0.01213   0.00788  -0.1112   0.8760   0.0131
  -6.500  -0.1659   0.01135   0.00695  -0.1115   0.8625   0.0168
  -6.250  -0.1380   0.01120   0.00676  -0.1115   0.8483   0.0195
  -6.000  -0.1101   0.01133   0.00686  -0.1113   0.8342   0.0218
  -5.750  -0.0820   0.01131   0.00673  -0.1112   0.8203   0.0236
  -5.500  -0.0538   0.01128   0.00661  -0.1112   0.8056   0.0245
  -5.250  -0.0255   0.01119   0.00640  -0.1112   0.7895   0.0249
  -5.000   0.0031   0.01086   0.00590  -0.1114   0.7706   0.0257
  -4.750   0.0314   0.01078   0.00571  -0.1115   0.7464   0.0268
  -4.500   0.0595   0.01096   0.00577  -0.1114   0.7117   0.0276
  -4.250   0.0871   0.01142   0.00612  -0.1113   0.6709   0.0285
  -4.000   0.1154   0.01150   0.00605  -0.1113   0.6432   0.0294
  -3.750   0.1444   0.01109   0.00544  -0.1117   0.6251   0.0299
  -3.500   0.1734   0.01067   0.00483  -0.1120   0.6108   0.0302
  -3.250   0.2024   0.01032   0.00433  -0.1122   0.5982   0.0306
  -3.000   0.2313   0.01000   0.00389  -0.1125   0.5868   0.0309
  -2.750   0.2603   0.00975   0.00353  -0.1127   0.5763   0.0313
  -2.500   0.2891   0.00961   0.00330  -0.1129   0.5652   0.0319
  -2.250   0.3179   0.00942   0.00301  -0.1131   0.5539   0.0322
  -2.000   0.3468   0.00928   0.00279  -0.1133   0.5427   0.0325
  -1.750   0.3755   0.00919   0.00262  -0.1134   0.5307   0.0328
  -1.500   0.4045   0.00894   0.00229  -0.1137   0.5177   0.0341
  -1.250   0.4333   0.00886   0.00214  -0.1139   0.5044   0.0353
  -1.000   0.4619   0.00884   0.00207  -0.1140   0.4913   0.0363
  -0.750   0.4905   0.00884   0.00200  -0.1142   0.4767   0.0372
  -0.500   0.5190   0.00885   0.00194  -0.1143   0.4633   0.0381
  -0.250   0.5476   0.00885   0.00189  -0.1145   0.4509   0.0390
   0.000   0.5761   0.00888   0.00185  -0.1146   0.4370   0.0400
   0.250   0.6044   0.00894   0.00183  -0.1148   0.4203   0.0409
   0.500   0.6327   0.00900   0.00183  -0.1149   0.4068   0.0417
   0.750   0.6612   0.00903   0.00182  -0.1150   0.3973   0.0426
   1.000   0.6897   0.00903   0.00179  -0.1152   0.3891   0.0457
   1.250   0.7181   0.00907   0.00182  -0.1154   0.3808   0.0488
   1.500   0.7465   0.00911   0.00185  -0.1155   0.3737   0.0514
   1.750   0.7747   0.00918   0.00189  -0.1156   0.3653   0.0532
   2.000   0.8030   0.00923   0.00193  -0.1157   0.3581   0.0555
   2.500   0.8595   0.00934   0.00208  -0.1160   0.3433   0.0786
   2.750   0.8876   0.00940   0.00219  -0.1161   0.3366   0.1105
   3.000   0.9157   0.00946   0.00229  -0.1163   0.3312   0.1302
   3.250   0.9437   0.00955   0.00240  -0.1164   0.3239   0.1436
   3.500   0.9716   0.00965   0.00252  -0.1165   0.3175   0.1555
   3.750   0.9995   0.00972   0.00264  -0.1166   0.3122   0.1734
   4.000   1.0274   0.00981   0.00280  -0.1167   0.3061   0.2187
   4.500   1.0779   0.00885   0.00322  -0.1162   0.2844   1.0000
   4.750   1.1050   0.00908   0.00339  -0.1162   0.2697   1.0000
   5.000   1.1316   0.00940   0.00360  -0.1161   0.2492   1.0000
   5.250   1.1575   0.00983   0.00386  -0.1160   0.2199   1.0000
   5.500   1.1790   0.01100   0.00455  -0.1154   0.1296   1.0000
   5.750   1.2032   0.01167   0.00506  -0.1151   0.0982   1.0000
   6.000   1.2262   0.01252   0.00565  -0.1146   0.0462   1.0000
   6.250   1.2506   0.01308   0.00611  -0.1142   0.0260   1.0000
   6.500   1.2755   0.01355   0.00652  -0.1138   0.0154   1.0000
   6.750   1.3006   0.01395   0.00693  -0.1135   0.0114   1.0000
   7.000   1.3259   0.01428   0.00729  -0.1132   0.0105   1.0000
   7.250   1.3506   0.01468   0.00771  -0.1129   0.0092   1.0000
   7.500   1.3746   0.01517   0.00821  -0.1124   0.0078   1.0000
   7.750   1.3988   0.01558   0.00865  -0.1120   0.0072   1.0000
   8.000   1.4228   0.01600   0.00912  -0.1115   0.0066   1.0000
   8.250   1.4461   0.01648   0.00963  -0.1110   0.0060   1.0000
   8.500   1.4685   0.01703   0.01020  -0.1103   0.0055   1.0000
   8.750   1.4898   0.01768   0.01092  -0.1094   0.0051   1.0000
   9.000   1.5117   0.01822   0.01151  -0.1087   0.0049   1.0000
   9.250   1.5327   0.01881   0.01215  -0.1078   0.0046   1.0000
   9.500   1.5532   0.01941   0.01280  -0.1068   0.0043   1.0000
   9.750   1.5731   0.02001   0.01347  -0.1058   0.0040   1.0000
  10.000   1.5920   0.02066   0.01416  -0.1047   0.0038   1.0000
  10.250   1.6088   0.02146   0.01501  -0.1032   0.0036   1.0000
  10.500   1.6212   0.02254   0.01618  -0.1010   0.0034   1.0000
  10.750   1.6351   0.02336   0.01708  -0.0991   0.0033   1.0000
  11.000   1.6465   0.02424   0.01805  -0.0968   0.0032   1.0000
  11.250   1.6534   0.02521   0.01911  -0.0938   0.0031   1.0000
  11.500   1.6589   0.02633   0.02031  -0.0908   0.0030   1.0000
  11.750   1.6637   0.02762   0.02170  -0.0880   0.0029   1.0000
  12.000   1.6680   0.02906   0.02324  -0.0855   0.0029   1.0000
  12.250   1.6716   0.03069   0.02498  -0.0833   0.0028   1.0000
  12.500   1.6742   0.03252   0.02692  -0.0812   0.0027   1.0000
  12.750   1.6758   0.03461   0.02911  -0.0795   0.0027   1.0000
  13.000   1.6775   0.03685   0.03145  -0.0781   0.0026   1.0000
  13.250   1.6771   0.03944   0.03415  -0.0770   0.0025   1.0000
  13.500   1.6769   0.04219   0.03701  -0.0762   0.0025   1.0000
  13.750   1.6753   0.04526   0.04019  -0.0757   0.0024   1.0000
  14.000   1.6725   0.04866   0.04369  -0.0755   0.0024   1.0000
  14.250   1.6684   0.05239   0.04755  -0.0756   0.0024   1.0000
  14.500   1.6636   0.05634   0.05160  -0.0760   0.0023   1.0000
  14.750   1.6572   0.06054   0.05592  -0.0765   0.0023   1.0000
  15.000   1.6489   0.06510   0.06059  -0.0771   0.0023   1.0000
  15.250   1.6399   0.06983   0.06544  -0.0778   0.0022   1.0000
  15.500   1.6294   0.07482   0.07055  -0.0787   0.0022   1.0000
  15.750   1.6182   0.08006   0.07592  -0.0798   0.0022   1.0000
  16.000   1.6061   0.08551   0.08149  -0.0811   0.0022   1.0000
  16.250   1.5931   0.09117   0.08726  -0.0825   0.0021   1.0000
  16.500   1.5797   0.09699   0.09321  -0.0840   0.0021   1.0000
  16.750   1.5667   0.10288   0.09921  -0.0857   0.0021   1.0000
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