XFOIL         Version 6.94
  
 Calculated polar for: BE50 (original)                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.080     Re =     0.300 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
   1.000   0.6730   0.00774   0.00228  -0.1058  0.6824  1.0000
   1.500   0.7269   0.00812   0.00245  -0.1051  0.6360  1.0000
   2.000   0.7800   0.00857   0.00264  -0.1044  0.5813  1.0000
   2.500   0.8319   0.00917   0.00294  -0.1035  0.5126  1.0000
   3.000   0.8831   0.00989   0.00333  -0.1026  0.4330  1.0000
   3.500   0.9344   0.01070   0.00390  -0.1019  0.3873  1.0000
   4.000   0.9864   0.01144   0.00454  -0.1013  0.3577  1.0000
   4.500   1.0374   0.01219   0.00518  -0.1006  0.3183  1.0000
   5.000   1.0891   0.01276   0.00573  -0.1001  0.2796  1.0000
   5.500   1.1401   0.01343   0.00629  -0.0994  0.2267  1.0000
   6.000   1.1811   0.01554   0.00766  -0.0977  0.0934  1.0000
   6.500   1.2191   0.01828   0.01009  -0.0949  0.0208  1.0000
   7.000   1.2578   0.02068   0.01279  -0.0921  0.0168  1.0000
   7.500   1.2929   0.02314   0.01552  -0.0889  0.0151  1.0000
   8.000   1.3215   0.02625   0.01893  -0.0848  0.0143  1.0000
   8.500   1.3471   0.03000   0.02298  -0.0803  0.0139  1.0000
   9.000   1.3725   0.03487   0.02826  -0.0758  0.0143  1.0000
   9.500   1.3921   0.04154   0.03548  -0.0712  0.0153  1.0000
  10.000   1.3950   0.04766   0.04215  -0.0653  0.0154  1.0000
  10.500   1.3793   0.05372   0.04871  -0.0586  0.0154  1.0000
  11.000   1.3470   0.06296   0.05843  -0.0540  0.0161  1.0000