XFOIL         Version 6.94
  
 Calculated polar for: FX 78-K-140 A/20                                
  
 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   0.5517   0.01985   0.01457  -0.1010  0.7081  0.9788
   2.000   0.7346   0.02077   0.01551  -0.1088  0.6919  0.9957
   2.500   0.7972   0.02046   0.01520  -0.1108  0.6881  0.9988
   3.000   0.8579   0.01982   0.01455  -0.1119  0.6863  1.0000
   4.000   0.9386   0.01975   0.01468  -0.1071  0.6755  1.0000
   5.000   1.0051   0.01996   0.01517  -0.0999  0.6611  1.0000
   5.500   1.0507   0.01943   0.01478  -0.0980  0.6557  1.0000
   6.000   1.1488   0.01508   0.01048  -0.1030  0.6443  1.0000
   6.500   1.1893   0.01378   0.00933  -0.0994  0.6245  1.0000
   7.000   1.2053   0.01271   0.00811  -0.0906  0.5532  1.0000
   7.500   1.1672   0.01338   0.00841  -0.0729  0.4866  1.0000
   8.000   1.0919   0.01866   0.01282  -0.0566  0.3486  1.0000
   8.500   1.0759   0.02344   0.01705  -0.0512  0.2446  1.0000
   9.000   1.0144   0.03162   0.02376  -0.0421  0.0313  1.0000
   9.500   1.0343   0.03444   0.02668  -0.0400  0.0228  1.0000
  10.000   1.0389   0.03876   0.03120  -0.0367  0.0167  1.0000
  10.500   1.0539   0.04235   0.03497  -0.0347  0.0159  1.0000
  11.000   1.0635   0.04642   0.03911  -0.0323  0.0135  1.0000
  11.500   1.0778   0.04982   0.04261  -0.0288  0.0128  1.0000
  12.000   1.1117   0.05175   0.04469  -0.0258  0.0121  1.0000