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GOE 14 AIRFOIL (goe14-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 14 AIRFOIL (goe14-il)
Reynolds number: 1,000,000
Max Cl/Cd: 111.29 at α=8.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe14-il-1000000-n5.txt
Download as CSV file: xf-goe14-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 14 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  -0.1722   0.10000   0.09738  -0.0287   0.7283   0.0179
  -8.500  -0.1635   0.09715   0.09450  -0.0303   0.7195   0.0179
  -8.250  -0.1547   0.09435   0.09168  -0.0319   0.7114   0.0179
  -8.000  -0.1454   0.09160   0.08891  -0.0335   0.7029   0.0179
  -7.750  -0.1354   0.08916   0.08643  -0.0349   0.6937   0.0178
  -7.500  -0.1278   0.08550   0.08276  -0.0380   0.6850   0.0180
  -7.250  -0.1182   0.08274   0.07995  -0.0403   0.6746   0.0180
  -7.000  -0.1038   0.07923   0.07641  -0.0448   0.6634   0.0181
  -6.750  -0.0887   0.07631   0.07344  -0.0478   0.6514   0.0182
  -6.500  -0.0720   0.07414   0.07122  -0.0499   0.6364   0.0183
  -6.250  -0.0539   0.07188   0.06889  -0.0526   0.6182   0.0185
  -6.000  -0.0345   0.06949   0.06641  -0.0557   0.5968   0.0187
  -5.750  -0.0140   0.06696   0.06378  -0.0591   0.5757   0.0189
  -5.500   0.0081   0.06477   0.06150  -0.0622   0.5568   0.0203
  -5.250   0.0312   0.06184   0.05848  -0.0661   0.5407   0.0203
  -5.000   0.0596   0.05806   0.05459  -0.0718   0.5272   0.0207
  -4.750   0.0806   0.05606   0.05252  -0.0737   0.5137   0.0201
  -4.500   0.1071   0.05303   0.04941  -0.0775   0.5037   0.0196
  -4.250   0.1345   0.05024   0.04651  -0.0809   0.4933   0.0196
  -4.000   0.1626   0.04755   0.04373  -0.0841   0.4839   0.0197
  -3.750   0.1911   0.04499   0.04106  -0.0870   0.4743   0.0198
  -3.500   0.2202   0.04247   0.03845  -0.0897   0.4656   0.0198
  -3.250   0.2495   0.04006   0.03591  -0.0921   0.4556   0.0198
  -3.000   0.2797   0.03758   0.03331  -0.0943   0.4466   0.0202
  -2.750   0.3097   0.03520   0.03079  -0.0963   0.4376   0.0203
  -2.500   0.3419   0.03223   0.02765  -0.0984   0.4314   0.0206
  -2.250   0.3743   0.02909   0.02431  -0.1001   0.4252   0.0209
  -2.000   0.4036   0.02707   0.02213  -0.1011   0.4191   0.0210
  -1.750   0.4324   0.02552   0.02047  -0.1018   0.4133   0.0211
  -1.250   0.4963   0.01293   0.00637  -0.1038   0.4034   0.0237
  -1.000   0.5237   0.01162   0.00484  -0.1037   0.3976   0.0239
  -0.750   0.5515   0.01111   0.00423  -0.1036   0.3914   0.0242
  -0.500   0.5793   0.01089   0.00395  -0.1035   0.3851   0.0246
  -0.250   0.6073   0.01073   0.00376  -0.1034   0.3801   0.0250
   0.000   0.6353   0.01058   0.00357  -0.1033   0.3745   0.0255
   0.250   0.6631   0.01046   0.00341  -0.1032   0.3684   0.0259
   0.500   0.6910   0.01035   0.00325  -0.1031   0.3634   0.0263
   0.750   0.7189   0.01026   0.00313  -0.1029   0.3577   0.0267
   1.000   0.7466   0.01023   0.00305  -0.1028   0.3510   0.0271
   1.250   0.7744   0.01019   0.00298  -0.1027   0.3453   0.0275
   1.500   0.8022   0.01016   0.00293  -0.1025   0.3391   0.0282
   1.750   0.8298   0.01018   0.00293  -0.1024   0.3330   0.0289
   2.000   0.8576   0.01019   0.00292  -0.1023   0.3276   0.0297
   2.250   0.8851   0.01023   0.00293  -0.1021   0.3201   0.0307
   2.500   0.9125   0.01029   0.00296  -0.1020   0.3131   0.0322
   2.750   0.9402   0.01032   0.00298  -0.1019   0.3072   0.0341
   3.000   0.9675   0.01037   0.00302  -0.1018   0.3013   0.0372
   3.250   0.9949   0.01045   0.00311  -0.1016   0.2963   0.0453
   3.500   1.0224   0.01056   0.00324  -0.1015   0.2915   0.0527
   3.750   1.0495   0.01071   0.00335  -0.1013   0.2854   0.0570
   4.000   1.0766   0.01090   0.00354  -0.1012   0.2795   0.0591
   4.250   1.1037   0.01103   0.00365  -0.1010   0.2737   0.0613
   4.500   1.1303   0.01120   0.00379  -0.1008   0.2674   0.0631
   4.750   1.1572   0.01137   0.00396  -0.1006   0.2622   0.0647
   5.000   1.1840   0.01152   0.00410  -0.1005   0.2571   0.0667
   5.250   1.2104   0.01169   0.00424  -0.1002   0.2519   0.0683
   5.500   1.2368   0.01181   0.00436  -0.1001   0.2477   0.0692
   5.750   1.2636   0.01191   0.00448  -0.0999   0.2447   0.0699
   6.000   1.2900   0.01205   0.00461  -0.0997   0.2405   0.0708
   6.250   1.3158   0.01223   0.00478  -0.0995   0.2356   0.0718
   6.500   1.3417   0.01241   0.00495  -0.0992   0.2317   0.0729
   6.750   1.3680   0.01253   0.00510  -0.0991   0.2293   0.0737
   7.000   1.3939   0.01269   0.00527  -0.0988   0.2258   0.0744
   7.250   1.4193   0.01289   0.00546  -0.0985   0.2214   0.0752
   7.500   1.4443   0.01311   0.00567  -0.0982   0.2174   0.0763
   7.750   1.4698   0.01329   0.00588  -0.0979   0.2148   0.0776
   8.000   1.4952   0.01346   0.00608  -0.0977   0.2125   0.0791
   8.250   1.5202   0.01366   0.00630  -0.0973   0.2096   0.0803
   8.500   1.5447   0.01388   0.00654  -0.0969   0.2064   0.0815
   8.750   1.5686   0.01415   0.00681  -0.0965   0.2028   0.0830
   9.000   1.5925   0.01439   0.00708  -0.0960   0.1992   0.0851
   9.250   1.6164   0.01463   0.00734  -0.0956   0.1949   0.0876
   9.500   1.6388   0.01497   0.00766  -0.0949   0.1890   0.0904
   9.750   1.6611   0.01530   0.00799  -0.0943   0.1834   0.0947
  10.000   1.6823   0.01568   0.00836  -0.0935   0.1754   0.1018
  10.500   1.7170   0.01592   0.00963  -0.0911   0.1481   1.0000
  11.000   1.7437   0.01735   0.01094  -0.0873   0.1266   1.0000
  11.500   1.7718   0.01866   0.01224  -0.0839   0.1169   1.0000
  11.750   1.7856   0.01936   0.01294  -0.0823   0.1134   1.0000
  12.000   1.7980   0.02018   0.01377  -0.0807   0.1097   1.0000
  12.250   1.8117   0.02094   0.01456  -0.0793   0.1068   1.0000
  12.500   1.8252   0.02174   0.01540  -0.0780   0.1042   1.0000
  12.750   1.8360   0.02276   0.01643  -0.0766   0.1006   1.0000
  13.000   1.8451   0.02395   0.01764  -0.0751   0.0968   1.0000
  13.250   1.8574   0.02495   0.01868  -0.0740   0.0946   1.0000
  13.500   1.8681   0.02610   0.01986  -0.0729   0.0915   1.0000
  13.750   1.8744   0.02764   0.02141  -0.0716   0.0869   1.0000
  14.000   1.8813   0.02920   0.02300  -0.0705   0.0827   1.0000
  14.250   1.8817   0.03136   0.02514  -0.0691   0.0751   1.0000
  14.500   1.8768   0.03411   0.02787  -0.0677   0.0659   1.0000
  14.750   1.8684   0.03731   0.03107  -0.0664   0.0579   1.0000
  15.000   1.8606   0.04060   0.03439  -0.0654   0.0523   1.0000
  15.250   1.8529   0.04399   0.03783  -0.0647   0.0477   1.0000
  15.500   1.8417   0.04796   0.04186  -0.0642   0.0434   1.0000
  15.750   1.8270   0.05256   0.04652  -0.0641   0.0381   1.0000
  16.000   1.8010   0.05879   0.05280  -0.0643   0.0293   1.0000
  16.250   1.7746   0.06539   0.05947  -0.0651   0.0222   1.0000
  16.500   1.7506   0.07182   0.06599  -0.0659   0.0184   1.0000
  16.750   1.7335   0.07743   0.07170  -0.0668   0.0170   1.0000
  17.000   1.7175   0.08292   0.07729  -0.0678   0.0160   1.0000
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