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 =     0.450 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
   1.000   0.5256   0.00879   0.00343  -0.0765  0.5587  0.9253
   1.500   0.5612   0.00863   0.00317  -0.0733  0.5535  0.9039
   2.500   0.7037   0.00966   0.00409  -0.0794  0.5319  0.9530
   3.000   0.7337   0.01016   0.00389  -0.0741  0.4246  0.9693
   3.500   0.7647   0.00938   0.00366  -0.0696  0.5102  0.9161
   5.500   1.0812   0.01110   0.00538  -0.0909  0.4266  1.0000
   7.500   1.0810   0.01441   0.00756  -0.0502  0.2388  1.0000
   8.000   1.0802   0.01612   0.00904  -0.0408  0.1883  1.0000
  10.000   1.0584   0.02887   0.02101  -0.0164  0.0068  1.0000
  11.000   0.9577   0.03340   0.02376   0.0177  0.0103  0.1661