XFOIL         Version 6.94
  
 Calculated polar for: Eiffel 428 (Bleriot)                            
  
 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
 ------- -------- --------- --------- -------- ------- -------
   0.000   0.4916   0.01082   0.00230  -0.0817  0.4544  0.1991
   0.500   0.5758   0.00964   0.00259  -0.0889  0.3611  1.0000
   1.000   0.6122   0.01111   0.00322  -0.0857  0.1949  1.0000
   1.500   0.6566   0.01190   0.00364  -0.0837  0.1368  1.0000
   2.000   0.7041   0.01242   0.00409  -0.0822  0.1313  1.0000
   2.500   0.7511   0.01298   0.00463  -0.0807  0.1256  1.0000
   3.000   0.7950   0.01377   0.00541  -0.0787  0.1184  1.0000
   3.500   0.8396   0.01447   0.00611  -0.0769  0.1113  1.0000
   4.000   0.8859   0.01501   0.00669  -0.0754  0.1037  1.0000
   4.500   0.9346   0.01535   0.00709  -0.0742  0.0950  1.0000
   5.000   0.9841   0.01563   0.00724  -0.0732  0.0604  1.0000
   5.500   1.0200   0.01690   0.00859  -0.0699  0.0538  1.0000
   6.000   1.0457   0.01877   0.01057  -0.0652  0.0486  1.0000
   6.500   1.0659   0.02076   0.01261  -0.0597  0.0438  1.0000
   7.000   1.0831   0.02296   0.01484  -0.0539  0.0395  1.0000
   7.500   1.1111   0.02571   0.01755  -0.0503  0.0344  1.0000
   8.000   1.1462   0.02764   0.01961  -0.0476  0.0300  1.0000
   8.500   1.1932   0.03051   0.02262  -0.0468  0.0261  1.0000
   9.000   1.2287   0.03288   0.02511  -0.0447  0.0231  1.0000
   9.500   1.2886   0.03799   0.03065  -0.0461  0.0211  1.0000
  10.000   1.3129   0.04189   0.03502  -0.0422  0.0194  1.0000
  10.500   1.3271   0.04669   0.04028  -0.0377  0.0187  1.0000
  11.000   1.3158   0.05383   0.04812  -0.0309  0.0197  1.0000
  11.500   1.2893   0.06111   0.05594  -0.0251  0.0208  1.0000