XFOIL         Version 6.94
  
 Calculated polar for: FX 79-W-151 A                                   
  
 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
 ------- -------- --------- --------- -------- ------- -------
   1.500   0.6206   0.01114   0.00498  -0.0849  0.5771  0.9486
   2.500   0.7754   0.01194   0.00574  -0.0941  0.5567  0.9747
   3.500   0.8192   0.01177   0.00531  -0.0811  0.5318  0.9551
   4.000   0.8840   0.01206   0.00502  -0.0833  0.4402  0.9903
   4.500   0.8831   0.01191   0.00504  -0.0718  0.4495  0.9749
   5.000   1.0092   0.01246   0.00552  -0.0869  0.4169  1.0000
   5.500   1.0765   0.01283   0.00654  -0.0902  0.4660  1.0000
   6.500   0.9974   0.01508   0.00743  -0.0540  0.2641  1.0000
   7.000   0.8876   0.02113   0.01193  -0.0310  0.0121  1.0000
   8.000   1.1917   0.01456   0.00833  -0.0588  0.3944  1.0000
   8.500   1.0165   0.02215   0.01364  -0.0264  0.1010  1.0000
   9.000   1.1752   0.01702   0.01034  -0.0382  0.2929  1.0000
   9.500   1.0722   0.02494   0.01676  -0.0207  0.1026  1.0000
  10.500   1.0850   0.03124   0.02328  -0.0138  0.0505  1.0000
  11.000   1.0818   0.03558   0.02727  -0.0112  0.0246  1.0000
  12.000   1.0641   0.04659   0.03896  -0.0063  0.0107  1.0000
  12.500   1.0710   0.05085   0.04370  -0.0054  0.0168  1.0000