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GOE 428 AIRFOIL (goe428-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 428 AIRFOIL (goe428-il)
Reynolds number: 200,000
Max Cl/Cd: 77.28 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe428-il-200000.txt
Download as CSV file: xf-goe428-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 428 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.000  -0.3109   0.08827   0.08526  -0.0234   1.0000   0.0325
  -6.750  -0.3270   0.08742   0.08451  -0.0202   1.0000   0.0328
  -6.500  -0.3357   0.08599   0.08315  -0.0191   0.9991   0.0332
  -6.250  -0.2949   0.08070   0.07782  -0.0333   0.9913   0.0355
  -6.000  -0.2410   0.07527   0.07226  -0.0515   0.9838   0.0365
  -5.750  -0.2081   0.06901   0.06594  -0.0605   0.9759   0.0369
  -5.500  -0.1934   0.06369   0.06063  -0.0609   0.9719   0.0385
  -5.250  -0.1664   0.06010   0.05702  -0.0645   0.9652   0.0402
  -5.000  -0.1289   0.05582   0.05265  -0.0715   0.9592   0.0440
  -4.750  -0.0729   0.04868   0.04515  -0.0858   0.9514   0.0502
  -4.500  -0.0446   0.04568   0.04219  -0.0878   0.9458   0.0531
  -4.250   0.0143   0.04065   0.03654  -0.0980   0.9390   0.0628
  -4.000   0.0423   0.03684   0.03287  -0.1000   0.9310   0.0657
  -3.750   0.0817   0.03343   0.02899  -0.1039   0.9207   0.0770
  -3.500   0.1138   0.03109   0.02671  -0.1057   0.9142   0.0844
  -3.250   0.1429   0.02879   0.02420  -0.1068   0.9029   0.0962
  -3.000   0.1737   0.02639   0.02151  -0.1080   0.8921   0.1075
  -2.750   0.2149   0.01748   0.01087  -0.1078   0.8847   0.0511
  -2.500   0.2442   0.01634   0.00954  -0.1078   0.8734   0.0556
  -2.250   0.2730   0.01502   0.00789  -0.1074   0.8615   0.0574
  -2.000   0.3017   0.01437   0.00698  -0.1070   0.8495   0.0619
  -1.750   0.3290   0.01326   0.00579  -0.1065   0.8380   0.0662
  -1.500   0.3564   0.01277   0.00519  -0.1060   0.8261   0.0718
  -1.250   0.3832   0.01230   0.00466  -0.1054   0.8142   0.0797
  -1.000   0.4094   0.01198   0.00428  -0.1047   0.8016   0.0897
  -0.750   0.4351   0.01167   0.00407  -0.1040   0.7889   0.1198
  -0.500   0.4603   0.01126   0.00382  -0.1034   0.7765   0.1930
  -0.250   0.4853   0.01094   0.00371  -0.1028   0.7642   0.2657
   0.000   0.5279   0.00920   0.00361  -0.1057   0.7519   1.0000
   0.250   0.5534   0.00929   0.00349  -0.1049   0.7387   1.0000
   0.500   0.5789   0.00938   0.00340  -0.1042   0.7249   1.0000
   0.750   0.6043   0.00947   0.00334  -0.1034   0.7108   1.0000
   1.000   0.6297   0.00957   0.00330  -0.1027   0.6963   1.0000
   1.250   0.6550   0.00968   0.00328  -0.1020   0.6812   1.0000
   1.500   0.6802   0.00981   0.00328  -0.1012   0.6654   1.0000
   1.750   0.7052   0.00996   0.00330  -0.1005   0.6488   1.0000
   2.000   0.7301   0.01013   0.00334  -0.0997   0.6315   1.0000
   2.250   0.7548   0.01032   0.00341  -0.0989   0.6131   1.0000
   2.500   0.7792   0.01052   0.00351  -0.0981   0.5930   1.0000
   2.750   0.8034   0.01074   0.00360  -0.0973   0.5731   1.0000
   3.000   0.8275   0.01096   0.00372  -0.0964   0.5519   1.0000
   3.250   0.8517   0.01121   0.00388  -0.0956   0.5323   1.0000
   3.500   0.8758   0.01148   0.00403  -0.0949   0.5150   1.0000
   3.750   0.9003   0.01176   0.00423  -0.0942   0.4992   1.0000
   4.000   0.9248   0.01205   0.00445  -0.0936   0.4852   1.0000
   4.250   0.9495   0.01237   0.00472  -0.0930   0.4729   1.0000
   4.500   0.9742   0.01267   0.00501  -0.0924   0.4612   1.0000
   4.750   0.9990   0.01298   0.00531  -0.0919   0.4505   1.0000
   5.000   1.0238   0.01332   0.00562  -0.0914   0.4411   1.0000
   5.250   1.0485   0.01365   0.00597  -0.0908   0.4317   1.0000
   5.500   1.0734   0.01396   0.00634  -0.0903   0.4230   1.0000
   5.750   1.0974   0.01430   0.00667  -0.0897   0.4126   1.0000
   6.000   1.1195   0.01454   0.00693  -0.0887   0.3964   1.0000
   6.250   1.1415   0.01479   0.00721  -0.0877   0.3806   1.0000
   6.500   1.1630   0.01505   0.00752  -0.0866   0.3633   1.0000
   6.750   1.1846   0.01533   0.00784  -0.0855   0.3470   1.0000
   7.000   1.2050   0.01560   0.00816  -0.0842   0.3240   1.0000
   7.250   1.2221   0.01600   0.00845  -0.0824   0.2762   1.0000
   7.500   1.2258   0.01779   0.00941  -0.0790   0.1443   1.0000
   7.750   1.2256   0.02020   0.01117  -0.0752   0.0468   1.0000
   8.000   1.2362   0.02152   0.01243  -0.0726   0.0358   1.0000
   8.250   1.2476   0.02269   0.01376  -0.0700   0.0319   1.0000
   8.500   1.2577   0.02381   0.01507  -0.0673   0.0302   1.0000
   8.750   1.2626   0.02505   0.01646  -0.0639   0.0289   1.0000
   9.000   1.2654   0.02641   0.01795  -0.0603   0.0281   1.0000
   9.250   1.2656   0.02800   0.01966  -0.0568   0.0271   1.0000
   9.500   1.2649   0.02980   0.02154  -0.0536   0.0262   1.0000
   9.750   1.2620   0.03199   0.02382  -0.0506   0.0251   1.0000
  10.000   1.2599   0.03468   0.02656  -0.0478   0.0240   1.0000
  10.250   1.2697   0.03689   0.02883  -0.0459   0.0235   1.0000
  10.500   1.2850   0.03871   0.03075  -0.0445   0.0232   1.0000
  10.750   1.3046   0.04074   0.03289  -0.0434   0.0230   1.0000
  11.000   1.3327   0.04349   0.03580  -0.0430   0.0231   1.0000
  11.250   1.3827   0.04829   0.04082  -0.0454   0.0239   1.0000
  11.500   1.3974   0.05223   0.04509  -0.0445   0.0238   1.0000
  11.750   1.4024   0.05516   0.04827  -0.0425   0.0239   1.0000
  12.000   1.4025   0.05658   0.04987  -0.0397   0.0242   1.0000
  12.250   1.3970   0.05780   0.05133  -0.0367   0.0248   1.0000
  12.500   1.2877   0.05738   0.05150  -0.0292   0.0244   1.0000
  12.750   1.2728   0.06054   0.05492  -0.0277   0.0249   1.0000
  13.000   1.2490   0.06524   0.06003  -0.0268   0.0263   1.0000
  13.250   1.2182   0.07192   0.06712  -0.0270   0.0278   1.0000
  13.500   1.1932   0.07837   0.07388  -0.0278   0.0289   1.0000
  13.750   1.1678   0.08476   0.08051  -0.0293   0.0296   1.0000
  14.000   1.1415   0.09080   0.08677  -0.0314   0.0301   1.0000
  14.250   1.1084   0.09659   0.09279  -0.0343   0.0300   1.0000
  14.500   1.0815   0.10272   0.09909  -0.0379   0.0301   1.0000
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