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 =     0.450 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
   0.000   0.4774   0.01319   0.00354  -0.0805  0.0369  0.0378
   0.500   0.5276   0.01291   0.00316  -0.0798  0.0376  0.0371
   1.000   0.5778   0.01284   0.00296  -0.0792  0.0383  0.0387
   1.500   0.6276   0.01294   0.00294  -0.0786  0.0391  0.0494
   2.000   0.6750   0.01273   0.00319  -0.0778  0.0399  0.2548
   2.500   0.7710   0.01173   0.00377  -0.0881  0.0413  1.0000
   3.000   0.8158   0.01215   0.00407  -0.0865  0.0422  1.0000
   3.500   0.8596   0.01259   0.00443  -0.0847  0.0432  1.0000
   4.000   0.9020   0.01307   0.00486  -0.0826  0.0441  1.0000
   4.500   0.9403   0.01373   0.00552  -0.0798  0.0437  1.0000
   5.000   0.9663   0.01497   0.00673  -0.0749  0.0398  1.0000
   5.500   0.9910   0.01601   0.00778  -0.0698  0.0384  1.0000
   6.000   1.0026   0.01710   0.00891  -0.0622  0.0367  1.0000
   6.500   1.0158   0.01840   0.01028  -0.0554  0.0344  1.0000
   7.000   1.0299   0.02013   0.01214  -0.0495  0.0312  1.0000
   7.500   1.0401   0.02324   0.01546  -0.0437  0.0261  1.0000
   8.000   1.0755   0.02287   0.01529  -0.0426  0.0215  1.0000
   8.500   1.1145   0.02332   0.01581  -0.0412  0.0144  1.0000
   9.000   1.1085   0.02791   0.02062  -0.0345  0.0139  1.0000