XFOIL         Version 6.94
  
 Calculated polar for: FX 73-170                                       
  
 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
 ------- -------- --------- --------- -------- ------- -------
   0.000   0.4387   0.01314   0.00566  -0.1053  0.6931  0.0893
   1.000   0.1780   0.01901   0.00887  -0.0388  0.0329  0.0880
   1.500   0.2273   0.01959   0.00928  -0.0384  0.0273  0.0874
   2.000   0.6047   0.01030   0.00411  -0.0940  0.6573  0.6165
   2.500   0.3290   0.02069   0.01020  -0.0394  0.0272  0.0781
   3.000   0.6514   0.01041   0.00412  -0.0809  0.5965  0.6649
   3.500   0.4107   0.02228   0.01175  -0.0390  0.0261  0.0681
   4.000   0.7846   0.01146   0.00562  -0.0878  0.6431  0.6625
   4.500   0.6369   0.01702   0.00881  -0.0535  0.3922  0.0399