XFOIL         Version 6.94
  
 Calculated polar for: AH 80-129                                       
  
 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   0.5651   0.01280   0.00731  -0.1017  0.7222  0.9485
   1.000   0.6895   0.01094   0.00430  -0.1119  0.5516  0.9784
   2.500   0.8519   0.01261   0.00706  -0.1164  0.6928  0.9783
   3.500   0.8978   0.01192   0.00469  -0.1015  0.4060  1.0000
   4.000   0.9622   0.01083   0.00487  -0.1036  0.5680  0.9919
   4.500   0.8774   0.01096   0.00422  -0.0753  0.4886  0.9642