XFOIL         Version 6.94
  
 Calculated polar for: GOE 780 AIRFOIL                                 
  
 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
 ------- -------- --------- --------- -------- ------- -------
   1.500   0.1066   0.01420   0.00300   0.0137  0.0210  0.0249
   2.000   0.2270   0.01040   0.00246   0.0011  0.6664  0.1613
   3.000   0.2398   0.01455   0.00361   0.0195  0.0175  0.0595
   3.500   0.2087   0.01160   0.00339   0.0374  0.0300  0.8047