XFOIL         Version 6.94
  
 Calculated polar for: E63  (4.25%)                                    
  
 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   0.6338   0.01348   0.00747  -0.1667  0.9567  0.1572
   0.500   0.6988   0.01159   0.00727  -0.1686  0.9470  1.0000
   1.000   0.7753   0.01114   0.00668  -0.1725  0.9381  1.0000
   1.500   0.8524   0.01044   0.00597  -0.1763  0.9277  1.0000
   2.000   0.9245   0.00962   0.00517  -0.1789  0.9131  1.0000
   2.500   0.9946   0.00892   0.00459  -0.1809  0.8906  1.0000
   3.000   1.0942   0.00811   0.00378  -0.1893  0.8374  1.0000
   3.500   1.1455   0.00992   0.00395  -0.1870  0.5467  1.0000
   4.000   1.1775   0.01195   0.00510  -0.1822  0.3531  1.0000
   4.500   1.2103   0.01486   0.00663  -0.1785  0.1095  1.0000
   5.000   1.2495   0.01754   0.00894  -0.1750  0.0198  1.0000
   5.500   1.2917   0.01963   0.01135  -0.1718  0.0190  1.0000
   6.000   1.3304   0.02256   0.01466  -0.1681  0.0191  1.0000
   6.500   1.3751   0.02740   0.01986  -0.1653  0.0197  1.0000
   7.000   1.4258   0.03226   0.02516  -0.1635  0.0208  1.0000
   8.500   1.4931   0.05190   0.04723  -0.1464  0.0097  1.0000
   9.000   1.4748   0.06284   0.05907  -0.1366  0.0099  1.0000
   9.500   1.4327   0.07206   0.06884  -0.1260  0.0102  1.0000