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GOE 14 AIRFOIL (goe14-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 14 AIRFOIL (goe14-il)
Reynolds number: 1,000,000
Max Cl/Cd: 122.5 at α=9.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe14-il-1000000.txt
Download as CSV file: xf-goe14-il-1000000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.2228   0.11949   0.11774  -0.0219   0.9205   0.0176
 -10.250  -0.2164   0.11696   0.11512  -0.0224   0.8994   0.0180
 -10.000  -0.2092   0.11423   0.11231  -0.0233   0.8817   0.0185
  -9.750  -0.2017   0.11127   0.10929  -0.0248   0.8664   0.0188
  -9.500  -0.1951   0.10836   0.10633  -0.0268   0.8533   0.0189
  -9.250  -0.1889   0.10554   0.10345  -0.0289   0.8412   0.0190
  -8.750  -0.1733   0.09936   0.09719  -0.0312   0.8200   0.0191
  -8.500  -0.1636   0.09671   0.09450  -0.0318   0.8100   0.0191
  -8.250  -0.1537   0.09424   0.09201  -0.0327   0.8011   0.0192
  -8.000  -0.1436   0.09186   0.08958  -0.0339   0.7917   0.0194
  -7.750  -0.1333   0.08947   0.08717  -0.0352   0.7830   0.0195
  -7.500  -0.1227   0.08706   0.08474  -0.0367   0.7739   0.0197
  -7.250  -0.1117   0.08461   0.08226  -0.0384   0.7656   0.0199
  -7.000  -0.1006   0.08218   0.07981  -0.0405   0.7569   0.0202
  -6.750  -0.0858   0.07946   0.07705  -0.0435   0.7486   0.0205
  -6.500  -0.0692   0.07658   0.07415  -0.0470   0.7398   0.0211
  -6.250  -0.0457   0.07285   0.07034  -0.0542   0.7312   0.0219
  -6.000  -0.0193   0.06905   0.06650  -0.0621   0.7227   0.0219
  -5.500   0.0194   0.06262   0.05998  -0.0675   0.7040   0.0221
  -5.250   0.0390   0.06018   0.05748  -0.0694   0.6931   0.0222
  -5.000   0.0612   0.05781   0.05505  -0.0718   0.6809   0.0224
  -4.750   0.0850   0.05547   0.05264  -0.0745   0.6681   0.0226
  -4.500   0.1102   0.05313   0.05022  -0.0774   0.6530   0.0228
  -4.250   0.1363   0.05078   0.04777  -0.0803   0.6353   0.0232
  -4.000   0.1636   0.04843   0.04530  -0.0831   0.6150   0.0239
  -3.750   0.2078   0.04481   0.04142  -0.0898   0.5940   0.0251
  -3.500   0.2349   0.04169   0.03814  -0.0923   0.5723   0.0253
  -2.750   0.3086   0.03666   0.03278  -0.0955   0.5193   0.0259
  -2.500   0.3364   0.03506   0.03107  -0.0968   0.5073   0.0263
  -2.250   0.3650   0.03343   0.02930  -0.0980   0.4957   0.0269
  -2.000   0.4053   0.03107   0.02669  -0.1000   0.4867   0.0285
  -1.750   0.4324   0.02872   0.02420  -0.1011   0.4775   0.0288
  -1.500   0.4581   0.02745   0.02288  -0.1016   0.4695   0.0290
  -1.250   0.4848   0.02638   0.02171  -0.1021   0.4608   0.0293
  -1.000   0.5127   0.02529   0.02055  -0.1026   0.4537   0.0300
  -0.750   0.5485   0.02307   0.01803  -0.1029   0.4465   0.0324
  -0.500   0.5745   0.02204   0.01693  -0.1033   0.4390   0.0327
  -0.250   0.6015   0.02125   0.01608  -0.1036   0.4315   0.0331
   0.000   0.6290   0.02051   0.01524  -0.1037   0.4238   0.0338
   0.500   0.6935   0.01076   0.00417  -0.1033   0.4151   0.0318
   0.750   0.7210   0.01046   0.00375  -0.1031   0.4082   0.0322
   1.000   0.7486   0.01008   0.00331  -0.1030   0.4024   0.0332
   1.250   0.7765   0.01001   0.00323  -0.1029   0.3962   0.0343
   1.500   0.8039   0.00995   0.00310  -0.1027   0.3893   0.0353
   1.750   0.8319   0.00986   0.00298  -0.1026   0.3841   0.0362
   2.000   0.8596   0.00978   0.00289  -0.1025   0.3779   0.0378
   2.250   0.8870   0.00982   0.00289  -0.1023   0.3708   0.0396
   2.500   0.9150   0.00980   0.00288  -0.1022   0.3656   0.0423
   2.750   0.9426   0.00987   0.00295  -0.1021   0.3585   0.0466
   3.000   0.9701   0.01007   0.00315  -0.1019   0.3515   0.0519
   3.250   0.9979   0.01028   0.00335  -0.1018   0.3444   0.0566
   3.500   1.0250   0.01059   0.00363  -0.1016   0.3364   0.0595
   3.750   1.0527   0.01070   0.00374  -0.1015   0.3311   0.0627
   4.000   1.0799   0.01092   0.00395  -0.1013   0.3248   0.0650
   4.250   1.1067   0.01108   0.00405  -0.1011   0.3186   0.0686
   4.500   1.1340   0.01115   0.00415  -0.1011   0.3134   0.0708
   4.750   1.1607   0.01130   0.00428  -0.1009   0.3073   0.0739
   5.000   1.1872   0.01140   0.00436  -0.1007   0.3015   0.0776
   5.250   1.2141   0.01147   0.00444  -0.1006   0.2961   0.0798
   5.500   1.2402   0.01158   0.00452  -0.1003   0.2895   0.0812
   5.750   1.2667   0.01169   0.00462  -0.1001   0.2842   0.0825
   6.000   1.2932   0.01179   0.00472  -0.0999   0.2792   0.0832
   6.250   1.3191   0.01190   0.00480  -0.0997   0.2736   0.0841
   6.500   1.3451   0.01201   0.00492  -0.0995   0.2687   0.0858
   6.750   1.3714   0.01212   0.00505  -0.0993   0.2641   0.0870
   7.000   1.3970   0.01230   0.00522  -0.0991   0.2592   0.0881
   7.250   1.4221   0.01252   0.00542  -0.0987   0.2541   0.0894
   7.500   1.4482   0.01265   0.00558  -0.0986   0.2512   0.0908
   7.750   1.4737   0.01282   0.00577  -0.0983   0.2477   0.0922
   8.000   1.4987   0.01302   0.00597  -0.0980   0.2438   0.0944
   8.250   1.5228   0.01329   0.00623  -0.0975   0.2394   0.0965
   8.500   1.5481   0.01345   0.00644  -0.0972   0.2369   0.0990
   8.750   1.5731   0.01364   0.00666  -0.0969   0.2341   0.1015
   9.000   1.5974   0.01386   0.00689  -0.0965   0.2305   0.1070
   9.250   1.6203   0.01418   0.00720  -0.0960   0.2254   0.1150
   9.500   1.6427   0.01341   0.00768  -0.0955   0.2219   1.0000
   9.750   1.6668   0.01364   0.00793  -0.0951   0.2187   1.0000
  10.000   1.6897   0.01395   0.00822  -0.0945   0.2144   1.0000
  10.250   1.7108   0.01437   0.00861  -0.0937   0.2088   1.0000
  10.500   1.7341   0.01461   0.00888  -0.0932   0.2049   1.0000
  10.750   1.7555   0.01496   0.00923  -0.0925   0.1991   1.0000
  11.000   1.7751   0.01541   0.00966  -0.0915   0.1929   1.0000
  11.250   1.7957   0.01574   0.01000  -0.0906   0.1875   1.0000
  11.500   1.8112   0.01629   0.01051  -0.0889   0.1798   1.0000
  11.750   1.8283   0.01674   0.01097  -0.0876   0.1722   1.0000
  12.000   1.8415   0.01743   0.01161  -0.0858   0.1624   1.0000
  12.250   1.8523   0.01828   0.01240  -0.0838   0.1511   1.0000
  12.750   1.8720   0.02020   0.01426  -0.0800   0.1335   1.0000
  13.000   1.8799   0.02136   0.01540  -0.0781   0.1268   1.0000
  13.250   1.8906   0.02237   0.01644  -0.0766   0.1225   1.0000
  13.500   1.8984   0.02364   0.01772  -0.0750   0.1181   1.0000
  13.750   1.9071   0.02490   0.01901  -0.0737   0.1145   1.0000
  14.000   1.9176   0.02605   0.02021  -0.0725   0.1121   1.0000
  14.250   1.9256   0.02745   0.02165  -0.0713   0.1092   1.0000
  14.500   1.9306   0.02914   0.02338  -0.0701   0.1061   1.0000
  14.750   1.9357   0.03088   0.02516  -0.0689   0.1030   1.0000
  15.000   1.9438   0.03239   0.02673  -0.0681   0.1004   1.0000
  15.250   1.9472   0.03436   0.02875  -0.0671   0.0969   1.0000
  15.500   1.9454   0.03689   0.03131  -0.0660   0.0929   1.0000
  15.750   1.9488   0.03897   0.03345  -0.0653   0.0893   1.0000
  16.000   1.9435   0.04200   0.03649  -0.0645   0.0835   1.0000
  16.250   1.9362   0.04535   0.03987  -0.0638   0.0767   1.0000
  16.500   1.9196   0.04994   0.04446  -0.0634   0.0682   1.0000
  16.750   1.8993   0.05519   0.04974  -0.0633   0.0610   1.0000
  17.000   1.8779   0.06084   0.05545  -0.0636   0.0556   1.0000
  17.250   1.8557   0.06679   0.06146  -0.0642   0.0508   1.0000
  17.500   1.8317   0.07311   0.06786  -0.0651   0.0463   1.0000
  17.750   1.8062   0.07975   0.07459  -0.0661   0.0424   1.0000
  18.000   1.7799   0.08661   0.08153  -0.0674   0.0381   1.0000
  18.250   1.7523   0.09379   0.08878  -0.0689   0.0333   1.0000
  18.500   1.7221   0.10149   0.09656  -0.0708   0.0281   1.0000
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