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 =     0.450 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
   0.000   0.7007   0.00894   0.00543  -0.1793  0.9521  0.8956
   0.500   0.7687   0.00840   0.00477  -0.1814  0.9428  1.0000
   1.000   0.8377   0.00785   0.00416  -0.1837  0.9328  1.0000
   1.500   0.9078   0.00720   0.00349  -0.1861  0.9205  1.0000
   2.000   0.9778   0.00674   0.00308  -0.1886  0.8965  1.0000
   2.500   1.0723   0.00640   0.00262  -0.1966  0.8408  1.0000
   3.000   1.1189   0.00776   0.00294  -0.1937  0.6382  1.0000
   3.500   1.1527   0.00942   0.00372  -0.1890  0.4618  1.0000
   4.000   1.1907   0.01131   0.00473  -0.1858  0.2799  1.0000
   4.500   1.2292   0.01360   0.00602  -0.1830  0.0956  1.0000
   5.000   1.2709   0.01566   0.00766  -0.1802  0.0192  1.0000
   5.500   1.3146   0.01744   0.00972  -0.1774  0.0162  1.0000
   6.000   1.3552   0.01960   0.01214  -0.1741  0.0154  1.0000
   6.500   1.3938   0.02274   0.01557  -0.1703  0.0153  1.0000
   7.000   1.4373   0.02616   0.01936  -0.1675  0.0142  1.0000
   7.500   1.4782   0.02982   0.02332  -0.1648  0.0112  1.0000
   8.000   1.5122   0.03536   0.02967  -0.1603  0.0078  1.0000
   8.500   1.5335   0.04200   0.03705  -0.1543  0.0066  1.0000
   9.000   1.5053   0.05920   0.05574  -0.1407  0.0088  1.0000