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GOE 628 AIRFOIL (goe628-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 628 AIRFOIL (goe628-il)
Reynolds number: 100,000
Max Cl/Cd: 47.54 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe628-il-100000-n5.txt
Download as CSV file: xf-goe628-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 628 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.4763   0.04911   0.04321  -0.1070   0.9450   0.0727
 -10.250  -0.4819   0.04307   0.03658  -0.1132   0.9306   0.0732
 -10.000  -0.4684   0.03953   0.03259  -0.1161   0.9204   0.0738
  -9.750  -0.4465   0.03794   0.03093  -0.1167   0.9104   0.0746
  -9.500  -0.4198   0.03629   0.02918  -0.1182   0.9025   0.0757
  -9.250  -0.3987   0.03474   0.02744  -0.1186   0.8922   0.0767
  -9.000  -0.3733   0.03308   0.02557  -0.1196   0.8838   0.0776
  -8.750  -0.3518   0.03165   0.02393  -0.1195   0.8735   0.0784
  -8.500  -0.3257   0.03025   0.02230  -0.1201   0.8650   0.0793
  -8.250  -0.3027   0.02908   0.02093  -0.1199   0.8552   0.0802
  -8.000  -0.2764   0.02796   0.01957  -0.1200   0.8465   0.0814
  -7.750  -0.2515   0.02707   0.01861  -0.1198   0.8373   0.0826
  -7.500  -0.2253   0.02628   0.01779  -0.1197   0.8285   0.0838
  -7.250  -0.1992   0.02554   0.01698  -0.1195   0.8201   0.0851
  -7.000  -0.1743   0.02484   0.01619  -0.1191   0.8109   0.0865
  -6.750  -0.1466   0.02414   0.01536  -0.1190   0.8035   0.0879
  -6.500  -0.1229   0.02357   0.01469  -0.1183   0.7939   0.0895
  -6.250  -0.0940   0.02294   0.01394  -0.1184   0.7873   0.0913
  -6.000  -0.0717   0.02249   0.01348  -0.1175   0.7777   0.0935
  -5.750  -0.0442   0.02198   0.01289  -0.1174   0.7704   0.0966
  -5.500  -0.0193   0.02157   0.01237  -0.1168   0.7622   0.0999
  -5.250   0.0060   0.02111   0.01188  -0.1163   0.7542   0.1037
  -5.000   0.0336   0.02065   0.01133  -0.1161   0.7473   0.1092
  -4.750   0.0569   0.02027   0.01095  -0.1153   0.7385   0.1160
  -4.500   0.0845   0.01980   0.01045  -0.1152   0.7314   0.1287
  -4.250   0.1085   0.01945   0.01017  -0.1145   0.7228   0.1498
  -4.000   0.1348   0.01917   0.00994  -0.1141   0.7141   0.1785
  -3.750   0.1610   0.01906   0.00982  -0.1135   0.7050   0.2038
  -3.500   0.1869   0.01901   0.00972  -0.1129   0.6953   0.2236
  -3.250   0.2140   0.01899   0.00961  -0.1124   0.6866   0.2404
  -3.000   0.2390   0.01904   0.00962  -0.1116   0.6772   0.2571
  -2.750   0.2678   0.01907   0.00951  -0.1114   0.6702   0.2733
  -2.500   0.2911   0.01916   0.00958  -0.1104   0.6608   0.2857
  -2.250   0.3182   0.01918   0.00954  -0.1099   0.6532   0.2970
  -2.000   0.3433   0.01924   0.00950  -0.1092   0.6449   0.3094
  -1.750   0.3686   0.01929   0.00955  -0.1084   0.6365   0.3203
  -1.500   0.3951   0.01933   0.00951  -0.1079   0.6288   0.3324
  -1.250   0.4191   0.01940   0.00955  -0.1069   0.6197   0.3445
  -1.000   0.4465   0.01937   0.00946  -0.1065   0.6125   0.3547
  -0.750   0.4694   0.01941   0.00948  -0.1054   0.6026   0.3644
  -0.500   0.4961   0.01935   0.00935  -0.1049   0.5948   0.3724
  -0.250   0.5197   0.01937   0.00937  -0.1040   0.5853   0.3804
   0.000   0.5458   0.01933   0.00924  -0.1034   0.5770   0.3887
   0.250   0.5695   0.01934   0.00926  -0.1025   0.5673   0.3965
   0.500   0.5954   0.01934   0.00915  -0.1019   0.5585   0.4057
   0.750   0.6188   0.01935   0.00920  -0.1009   0.5486   0.4134
   1.000   0.6444   0.01936   0.00913  -0.1003   0.5398   0.4233
   1.250   0.6677   0.01941   0.00921  -0.0993   0.5299   0.4318
   1.500   0.6926   0.01944   0.00916  -0.0986   0.5209   0.4424
   1.750   0.7153   0.01952   0.00928  -0.0975   0.5104   0.4524
   2.000   0.7409   0.01958   0.00925  -0.0969   0.5014   0.4646
   2.250   0.7634   0.01970   0.00942  -0.0959   0.4907   0.4767
   2.500   0.7882   0.01978   0.00946  -0.0952   0.4823   0.4913
   2.750   0.8105   0.01991   0.00966  -0.0942   0.4722   0.5082
   3.000   0.8343   0.02000   0.00974  -0.0934   0.4639   0.5298
   3.250   0.8555   0.02011   0.00999  -0.0922   0.4542   0.5598
   3.500   0.8775   0.02007   0.01010  -0.0910   0.4465   0.6225
   4.000   0.9429   0.02014   0.01058  -0.0929   0.4292   1.0000
   4.250   0.9634   0.02052   0.01092  -0.0917   0.4214   1.0000
   4.500   0.9848   0.02087   0.01117  -0.0906   0.4146   1.0000
   4.750   1.0064   0.02125   0.01144  -0.0896   0.4083   1.0000
   5.000   1.0261   0.02166   0.01181  -0.0883   0.4014   1.0000
   5.250   1.0475   0.02205   0.01209  -0.0872   0.3956   1.0000
   5.500   1.0685   0.02248   0.01246  -0.0862   0.3902   1.0000
   5.750   1.0881   0.02294   0.01292  -0.0849   0.3847   1.0000
   6.000   1.1087   0.02338   0.01330  -0.0838   0.3797   1.0000
   6.250   1.1320   0.02381   0.01360  -0.0831   0.3754   1.0000
   6.500   1.1482   0.02433   0.01418  -0.0814   0.3702   1.0000
   6.750   1.1659   0.02482   0.01467  -0.0799   0.3653   1.0000
   7.000   1.1860   0.02530   0.01510  -0.0787   0.3612   1.0000
   7.250   1.2109   0.02578   0.01547  -0.0784   0.3577   1.0000
   7.500   1.2245   0.02640   0.01619  -0.0764   0.3535   1.0000
   7.750   1.2403   0.02699   0.01683  -0.0747   0.3492   1.0000
   8.000   1.2584   0.02755   0.01738  -0.0734   0.3453   1.0000
   8.250   1.2804   0.02807   0.01784  -0.0727   0.3418   1.0000
   8.500   1.2995   0.02870   0.01848  -0.0717   0.3384   1.0000
   8.750   1.3114   0.02947   0.01936  -0.0697   0.3348   1.0000
   9.000   1.3254   0.03021   0.02016  -0.0680   0.3311   1.0000
   9.250   1.3422   0.03087   0.02085  -0.0668   0.3276   1.0000
   9.500   1.3633   0.03144   0.02138  -0.0661   0.3244   1.0000
   9.750   1.3829   0.03213   0.02208  -0.0653   0.3214   1.0000
  10.000   1.3878   0.03320   0.02332  -0.0627   0.3179   1.0000
  10.250   1.3963   0.03421   0.02444  -0.0608   0.3144   1.0000
  10.500   1.4090   0.03508   0.02536  -0.0593   0.3110   1.0000
  10.750   1.4268   0.03577   0.02605  -0.0584   0.3078   1.0000
  11.000   1.4535   0.03625   0.02647  -0.0584   0.3049   1.0000
  11.250   1.4458   0.03794   0.02839  -0.0552   0.3014   1.0000
  11.500   1.4442   0.03954   0.03015  -0.0528   0.2977   1.0000
  11.750   1.4499   0.04082   0.03151  -0.0511   0.2939   1.0000
  12.000   1.4651   0.04163   0.03234  -0.0502   0.2906   1.0000
  12.250   1.4911   0.04195   0.03259  -0.0500   0.2874   1.0000
  12.500   1.4686   0.04495   0.03588  -0.0469   0.2837   1.0000
  12.750   1.4565   0.04765   0.03877  -0.0449   0.2798   1.0000
  13.000   1.4574   0.04957   0.04079  -0.0437   0.2762   1.0000
  13.250   1.4727   0.05043   0.04166  -0.0430   0.2730   1.0000
  13.500   1.4957   0.05080   0.04200  -0.0426   0.2703   1.0000
  13.750   1.4426   0.05744   0.04902  -0.0406   0.2658   1.0000
  14.000   1.4050   0.06360   0.05542  -0.0401   0.2611   1.0000
  14.250   1.4110   0.06548   0.05735  -0.0397   0.2577   1.0000
  14.500   1.4435   0.06451   0.05634  -0.0391   0.2551   1.0000
  15.000   1.2795   0.09122   0.08359  -0.0441   0.2395   1.0000
  15.250   1.3222   0.08807   0.08043  -0.0425   0.2386   1.0000
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