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BE50 (original) (be50-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: BE50 (original) (be50-il)
Reynolds number: 50,000
Max Cl/Cd: 38.34 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-be50-il-50000.txt
Download as CSV file: xf-be50-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: BE50 (original)                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3844   0.10048   0.09392  -0.0167   1.0000   0.1883
  -7.750  -0.3710   0.09627   0.08972  -0.0149   1.0000   0.1976
  -7.500  -0.3755   0.09447   0.08805  -0.0173   1.0000   0.2031
  -7.250  -0.3663   0.09105   0.08467  -0.0159   1.0000   0.2133
  -6.750  -0.3619   0.08586   0.07966  -0.0178   1.0000   0.2324
  -6.500  -0.3581   0.08351   0.07738  -0.0189   1.0000   0.2462
  -6.250  -0.3520   0.08061   0.07455  -0.0183   1.0000   0.2609
  -6.000  -0.3454   0.07765   0.07162  -0.0174   1.0000   0.2759
  -5.750  -0.3385   0.07467   0.06870  -0.0162   1.0000   0.2911
  -5.500  -0.3312   0.07170   0.06579  -0.0143   1.0000   0.3073
  -5.250  -0.3238   0.06897   0.06312  -0.0125   1.0000   0.3259
  -5.000  -0.3169   0.06650   0.06070  -0.0125   1.0000   0.3499
  -4.750  -0.3094   0.06416   0.05841  -0.0115   1.0000   0.3775
  -4.500  -0.3041   0.06155   0.05588  -0.0078   1.0000   0.4073
  -4.250  -0.3002   0.05898   0.05339  -0.0029   1.0000   0.4399
  -3.750  -0.0958   0.03848   0.03068  -0.0682   1.0000   0.1746
  -3.500  -0.0530   0.03427   0.02574  -0.0729   1.0000   0.1554
  -3.250  -0.0194   0.03160   0.02263  -0.0751   1.0000   0.1538
  -3.000   0.0146   0.02945   0.01993  -0.0769   1.0000   0.1559
  -2.750   0.0473   0.02758   0.01758  -0.0781   1.0000   0.1565
  -2.500   0.0776   0.02604   0.01568  -0.0788   1.0000   0.1598
  -2.250   0.1068   0.02488   0.01435  -0.0793   1.0000   0.1679
  -2.000   0.1358   0.02402   0.01328  -0.0797   1.0000   0.1871
  -1.750   0.1660   0.02300   0.01224  -0.0801   1.0000   0.2172
  -1.500   0.2040   0.02103   0.01129  -0.0817   1.0000   0.3960
  -1.250   0.2129   0.01883   0.01065  -0.0772   1.0000   1.0000
  -1.000   0.2378   0.01936   0.01062  -0.0776   1.0000   1.0000
  -0.750   0.2611   0.01995   0.01087  -0.0779   1.0000   1.0000
  -0.500   0.2834   0.02061   0.01127  -0.0782   1.0000   1.0000
  -0.250   0.3051   0.02135   0.01177  -0.0785   1.0000   1.0000
   0.000   0.3261   0.02215   0.01241  -0.0789   1.0000   1.0000
   0.250   0.3464   0.02304   0.01316  -0.0793   1.0000   1.0000
   0.500   0.3795   0.02403   0.01403  -0.0821   0.9945   1.0000
   0.750   0.4391   0.02495   0.01481  -0.0894   0.9737   1.0000
   1.000   0.4971   0.02567   0.01546  -0.0959   0.9522   1.0000
   1.250   0.5527   0.02614   0.01592  -0.1014   0.9290   1.0000
   1.500   0.6023   0.02639   0.01620  -0.1054   0.9037   1.0000
   1.750   0.6533   0.02633   0.01621  -0.1090   0.8779   1.0000
   2.000   0.7053   0.02591   0.01591  -0.1119   0.8522   1.0000
   2.250   0.7527   0.02525   0.01534  -0.1132   0.8257   1.0000
   2.500   0.7929   0.02464   0.01484  -0.1131   0.7968   1.0000
   2.750   0.8275   0.02422   0.01446  -0.1119   0.7657   1.0000
   3.000   0.8590   0.02399   0.01424  -0.1103   0.7338   1.0000
   3.250   0.8880   0.02399   0.01421  -0.1086   0.7025   1.0000
   3.500   0.9151   0.02424   0.01447  -0.1069   0.6724   1.0000
   3.750   0.9406   0.02469   0.01490  -0.1053   0.6437   1.0000
   4.000   0.9654   0.02527   0.01549  -0.1039   0.6168   1.0000
   4.250   0.9904   0.02591   0.01613  -0.1026   0.5920   1.0000
   4.500   1.0161   0.02650   0.01677  -0.1014   0.5691   1.0000
   4.750   1.0395   0.02739   0.01777  -0.1003   0.5459   1.0000
   5.000   1.0655   0.02809   0.01846  -0.0991   0.5255   1.0000
   5.250   1.0879   0.02922   0.01976  -0.0981   0.5040   1.0000
   5.500   1.1122   0.03018   0.02086  -0.0970   0.4842   1.0000
   5.750   1.1363   0.03122   0.02202  -0.0960   0.4655   1.0000
   6.000   1.1579   0.03250   0.02354  -0.0949   0.4462   1.0000
   6.250   1.1816   0.03357   0.02476  -0.0937   0.4278   1.0000
   6.500   1.2058   0.03465   0.02595  -0.0925   0.4095   1.0000
   6.750   1.2253   0.03598   0.02761  -0.0910   0.3875   1.0000
   7.000   1.2458   0.03539   0.02680  -0.0882   0.3497   1.0000
   7.250   1.2572   0.03440   0.02566  -0.0847   0.3028   1.0000
   7.500   1.2627   0.03372   0.02495  -0.0807   0.2531   1.0000
   7.750   1.2539   0.03481   0.02568  -0.0753   0.1753   1.0000
   8.000   1.2541   0.03792   0.02814  -0.0716   0.1269   1.0000
   8.250   1.2676   0.04087   0.03104  -0.0693   0.1065   1.0000
   8.500   1.2851   0.04381   0.03407  -0.0675   0.0950   1.0000
   8.750   1.3027   0.04685   0.03715  -0.0661   0.0867   1.0000
   9.000   1.3189   0.04997   0.04054  -0.0646   0.0810   1.0000
   9.250   1.3410   0.05423   0.04481  -0.0640   0.0776   1.0000
   9.500   1.3478   0.05834   0.04947  -0.0618   0.0767   1.0000
   9.750   1.3492   0.06273   0.05439  -0.0595   0.0762   1.0000
  10.000   1.3448   0.06728   0.05940  -0.0572   0.0761   1.0000
  10.250   1.3349   0.07186   0.06438  -0.0549   0.0762   1.0000
  10.500   1.3194   0.07627   0.06910  -0.0525   0.0764   1.0000
  10.750   1.3011   0.08079   0.07387  -0.0507   0.0767   1.0000
  11.000   1.2816   0.08575   0.07905  -0.0499   0.0771   1.0000
  11.250   1.2626   0.09124   0.08471  -0.0501   0.0775   1.0000
  11.500   1.1689   0.10536   0.09936  -0.0622   0.0823   1.0000
  11.750   1.1253   0.11956   0.11360  -0.0723   0.0861   1.0000
  12.000   1.1060   0.12994   0.12394  -0.0780   0.0882   1.0000
  12.250   1.0969   0.13808   0.13200  -0.0815   0.0893   1.0000
  12.500   0.8347   0.14695   0.14089  -0.0722   0.1245   1.0000
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