XFOIL         Version 6.94
  
 Calculated polar for: FX 78-K-140/20                                  
  
 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
 ------- -------- --------- --------- -------- ------- -------
   0.000   0.4839   0.02016   0.01509  -0.0965  0.7112  0.9841
   0.500   0.5788   0.01986   0.01465  -0.1051  0.7095  0.9947
   1.000   0.6538   0.01927   0.01397  -0.1094  0.7080  1.0000
   2.000   0.7280   0.01980   0.01451  -0.1046  0.6972  1.0000
   3.000   0.7801   0.02134   0.01616  -0.0967  0.6800  1.0000
   3.500   0.8255   0.02091   0.01575  -0.0947  0.6770  1.0000
   4.000   0.8686   0.02066   0.01554  -0.0925  0.6734  1.0000
   5.000   0.9643   0.01953   0.01457  -0.0892  0.6647  1.0000
   6.000   1.0537   0.01867   0.01403  -0.0850  0.6520  1.0000
   6.500   1.1278   0.01547   0.01096  -0.0859  0.6387  1.0000
   7.000   1.1726   0.01340   0.00895  -0.0822  0.6002  1.0000
   7.500   1.1675   0.01389   0.00897  -0.0708  0.5039  1.0000
   8.000   1.1145   0.01738   0.01185  -0.0552  0.4146  1.0000
   8.500   1.0512   0.02350   0.01702  -0.0420  0.2707  1.0000
   9.000   0.9819   0.03132   0.02326  -0.0307  0.0418  1.0000
   9.500   0.9907   0.03469   0.02659  -0.0269  0.0193  1.0000
  10.000   1.0108   0.03735   0.02944  -0.0244  0.0178  1.0000
  10.500   1.0154   0.04143   0.03371  -0.0210  0.0151  1.0000
  11.000   1.0208   0.04555   0.03799  -0.0176  0.0140  1.0000
  11.500   1.0361   0.04880   0.04136  -0.0147  0.0139  1.0000
  12.000   1.0592   0.05138   0.04408  -0.0121  0.0121  1.0000
  12.500   1.1054   0.05274   0.04546  -0.0083  0.0099  1.0000
  13.000   1.1572   0.05592   0.04934  -0.0053  0.0124  1.0000