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GOE 396 AIRFOIL (goe396-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 396 AIRFOIL (goe396-il)
Reynolds number: 1,000,000
Max Cl/Cd: 141.69 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe396-il-1000000.txt
Download as CSV file: xf-goe396-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 396 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3135   0.10365   0.10207  -0.0274   1.0000   0.0059
  -8.500  -0.3103   0.10100   0.09943  -0.0276   1.0000   0.0059
  -8.250  -0.3077   0.09858   0.09703  -0.0276   1.0000   0.0059
  -8.000  -0.2129   0.07760   0.07618  -0.0380   0.9933   0.0062
  -7.750  -0.2012   0.07372   0.07230  -0.0406   0.9876   0.0063
  -7.500  -0.1873   0.06981   0.06839  -0.0437   0.9820   0.0065
  -7.250  -0.1725   0.06579   0.06436  -0.0475   0.9736   0.0066
  -7.000  -0.2496   0.07995   0.07847  -0.0438   0.9843   0.0062
  -6.750  -0.2299   0.07629   0.07481  -0.0481   0.9763   0.0064
  -6.500  -0.2020   0.07230   0.07079  -0.0548   0.9700   0.0066
  -6.250  -0.1701   0.06822   0.06668  -0.0624   0.9621   0.0070
  -4.250   0.0576   0.03619   0.03376  -0.1037   0.8422   0.0113
  -4.000   0.0819   0.03445   0.03192  -0.1048   0.8342   0.0123
  -3.750   0.1093   0.03177   0.02913  -0.1065   0.8263   0.0137
  -2.750   0.2169   0.01011   0.00534  -0.1083   0.7986   0.0100
  -2.500   0.2413   0.00834   0.00316  -0.1074   0.7912   0.0123
  -2.250   0.2681   0.00810   0.00286  -0.1071   0.7839   0.0139
  -2.000   0.2948   0.00787   0.00254  -0.1067   0.7767   0.0158
  -1.750   0.3208   0.00739   0.00196  -0.1062   0.7681   0.0195
  -1.500   0.3474   0.00725   0.00178  -0.1058   0.7588   0.0238
  -1.250   0.3743   0.00728   0.00176  -0.1055   0.7496   0.0265
  -1.000   0.4003   0.00692   0.00133  -0.1051   0.7400   0.0339
  -0.750   0.4269   0.00683   0.00118  -0.1047   0.7297   0.0376
  -0.500   0.4533   0.00679   0.00109  -0.1044   0.7171   0.0393
  -0.250   0.4794   0.00667   0.00087  -0.1039   0.7038   0.0441
   0.000   0.5053   0.00655   0.00077  -0.1035   0.6905   0.0645
   0.250   0.5312   0.00648   0.00078  -0.1031   0.6767   0.1148
   0.500   0.5574   0.00650   0.00078  -0.1027   0.6625   0.1283
   0.750   0.5835   0.00653   0.00078  -0.1023   0.6484   0.1406
   1.000   0.6095   0.00657   0.00079  -0.1019   0.6343   0.1554
   1.250   0.6355   0.00659   0.00083  -0.1016   0.6209   0.1775
   1.500   0.6614   0.00661   0.00088  -0.1012   0.6071   0.2132
   1.750   0.6869   0.00661   0.00095  -0.1008   0.5918   0.2671
   2.000   0.7118   0.00652   0.00106  -0.1003   0.5769   0.3844
   2.250   0.7696   0.00547   0.00122  -0.1078   0.5573   1.0000
   2.500   0.7949   0.00561   0.00129  -0.1072   0.5400   1.0000
   2.750   0.8184   0.00587   0.00139  -0.1064   0.5042   1.0000
   3.000   0.8415   0.00617   0.00151  -0.1055   0.4654   1.0000
   3.250   0.8629   0.00664   0.00172  -0.1043   0.4052   1.0000
   3.500   0.8822   0.00732   0.00200  -0.1028   0.3244   1.0000
   3.750   0.8934   0.00880   0.00266  -0.1001   0.1501   1.0000
   4.000   0.9156   0.00925   0.00295  -0.0991   0.1193   1.0000
   4.250   0.9390   0.00958   0.00318  -0.0984   0.0982   1.0000
   4.500   0.9565   0.01052   0.00372  -0.0966   0.0162   1.0000
   4.750   0.9802   0.01084   0.00414  -0.0957   0.0128   1.0000
   5.000   1.0026   0.01129   0.00471  -0.0946   0.0110   1.0000
   5.250   1.0256   0.01166   0.00511  -0.0936   0.0102   1.0000
   5.500   1.0478   0.01209   0.00559  -0.0926   0.0092   1.0000
   5.750   1.0691   0.01263   0.00621  -0.0913   0.0085   1.0000
   6.000   1.0896   0.01322   0.00686  -0.0900   0.0078   1.0000
   6.250   1.1084   0.01397   0.00769  -0.0883   0.0069   1.0000
   6.500   1.1183   0.01562   0.00946  -0.0851   0.0062   1.0000
   6.750   1.1312   0.01709   0.01100  -0.0824   0.0061   1.0000
   7.000   1.1490   0.01814   0.01211  -0.0805   0.0062   1.0000
   7.250   1.1681   0.01915   0.01319  -0.0790   0.0064   1.0000
   7.500   1.1860   0.02174   0.01583  -0.0774   0.0061   1.0000
   7.750   1.2079   0.02353   0.01771  -0.0764   0.0061   1.0000
   8.250   1.2457   0.02603   0.02060  -0.0734   0.0052   1.0000
   8.500   1.2645   0.02789   0.02263  -0.0718   0.0050   1.0000
   8.750   1.2814   0.03059   0.02558  -0.0698   0.0048   1.0000
   9.500   1.2833   0.04693   0.04298  -0.0595   0.0058   1.0000
   9.750   1.2811   0.04972   0.04601  -0.0560   0.0057   1.0000
  10.000   1.2755   0.05241   0.04891  -0.0523   0.0057   1.0000
  10.250   1.2648   0.05427   0.05097  -0.0477   0.0057   1.0000
  10.500   1.2504   0.05684   0.05368  -0.0434   0.0057   1.0000
  10.750   1.2371   0.05877   0.05577  -0.0399   0.0056   1.0000
  11.000   1.2468   0.05837   0.05549  -0.0379   0.0050   1.0000
  11.250   1.2326   0.06158   0.05885  -0.0360   0.0049   1.0000
  11.500   1.2166   0.06532   0.06275  -0.0348   0.0048   1.0000
  11.750   1.1990   0.06966   0.06724  -0.0346   0.0048   1.0000
  12.000   1.1804   0.07463   0.07235  -0.0352   0.0048   1.0000
  12.500   1.1400   0.08672   0.08470  -0.0398   0.0049   1.0000
  12.750   0.9737   0.10224   0.10044  -0.0454   0.0058   1.0000
  13.000   0.9461   0.10913   0.10745  -0.0503   0.0058   1.0000
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