XFOIL         Version 6.94
  
 Calculated polar for: FX 78-K-150/20                                  
  
 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   0.5241   0.01077   0.00327  -0.0741  0.6432  0.2035
   2.000   0.1934   0.01978   0.00967  -0.0057  0.0571  0.0393
   2.500   0.5716   0.01392   0.00702  -0.0644  0.6606  0.3051
   3.000   0.2707   0.02079   0.01047  -0.0032  0.0368  0.0452
   3.500   0.3067   0.01874   0.01062  -0.0011  0.0207  0.8411
   4.000   0.3746   0.02064   0.01118  -0.0039  0.1514  0.1902
   4.500   0.3855   0.02257   0.01331   0.0025  0.0637  0.1658