XFOIL         Version 6.94
  
 Calculated polar for: Eiffel 430 (Lachassgne)                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.026 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
   0.000  -0.0065   0.04349   0.03132  -0.0150  1.0000  0.3917
   0.250   0.0283   0.04281   0.03059  -0.0170  1.0000  0.4284
   0.500   0.1105   0.04260   0.03101  -0.0274  0.9755  0.5430
   0.750   0.2133   0.04279   0.03216  -0.0421  0.9461  1.0000
   1.000   0.2722   0.04446   0.03316  -0.0484  0.9142  1.0000
   1.250   0.3291   0.04626   0.03449  -0.0541  0.8818  1.0000
   1.500   0.3861   0.04794   0.03582  -0.0595  0.8453  1.0000
   1.750   0.4326   0.04941   0.03706  -0.0631  0.8092  1.0000
   2.000   0.4581   0.05103   0.03849  -0.0638  0.7784  1.0000
   2.250   0.4838   0.05281   0.04011  -0.0648  0.7560  1.0000
   2.500   0.5026   0.05482   0.04198  -0.0651  0.7403  1.0000
   2.750   0.5324   0.05670   0.04374  -0.0665  0.7280  1.0000
   3.000   0.5269   0.05921   0.04616  -0.0645  0.7185  1.0000
   3.250   0.5484   0.06126   0.04811  -0.0651  0.7093  1.0000
   3.500   0.5525   0.06366   0.05043  -0.0641  0.7021  1.0000
   3.750   0.5548   0.06610   0.05281  -0.0631  0.6962  1.0000
   4.000   0.5615   0.06865   0.05532  -0.0627  0.6931  1.0000
   4.250   0.5640   0.07138   0.05801  -0.0622  0.6929  1.0000
   4.500   0.5655   0.07412   0.06072  -0.0617  0.6935  1.0000
   4.750   0.5689   0.07681   0.06338  -0.0613  0.6934  1.0000
   5.000   0.5719   0.07950   0.06606  -0.0609  0.6937  1.0000