XFOIL         Version 6.94
  
 Calculated polar for: EPPLER 378 AIRFOIL                              
  
 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
 ------- -------- --------- --------- -------- ------- -------
   0.500   0.5640   0.02821   0.02180  -0.1023  0.5465  0.0136
   1.000   0.5278   0.03022   0.02364  -0.0864  0.5367  0.0131