XFOIL         Version 6.94
  
 Calculated polar for: AUGUST 160                                      
  
 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
 ------- -------- --------- --------- -------- ------- -------
   0.500   0.3869   0.01183   0.00364  -0.0209  0.3384  0.2884
   1.000   0.4352   0.01263   0.00314  -0.0180  0.3115  0.0393
   1.500   0.4816   0.01225   0.00374  -0.0165  0.3356  0.2411
   2.000   0.5259   0.01246   0.00363  -0.0137  0.3268  0.2023
   2.500   0.6272   0.01081   0.00433  -0.0241  0.3279  0.8845
   3.000   0.7325   0.01160   0.00487  -0.0340  0.3049  0.9509
   3.500   0.8389   0.01258   0.00515  -0.0445  0.2441  0.9739
   4.000   0.7718   0.01198   0.00524  -0.0198  0.3170  0.9018
   4.500   0.9520   0.01288   0.00613  -0.0447  0.3013  0.9771
   5.000   0.9884   0.01312   0.00575  -0.0416  0.2423  0.9814
   5.500   0.9855   0.01638   0.00807  -0.0335  0.0832  0.9906
   6.000   1.0217   0.01306   0.00633  -0.0262  0.2937  0.9546
   6.500   0.9033   0.01463   0.00549   0.0108  0.2830  0.0516
   7.000   0.8392   0.01959   0.00897   0.0257  0.0662  0.0412
   7.500   0.9978   0.01511   0.00634   0.0129  0.2760  0.1873
   8.000   1.2146   0.01449   0.00772  -0.0225  0.2706  0.9794
   8.500   1.3111   0.01548   0.00843  -0.0326  0.2494  1.0000
   9.000   1.3507   0.01598   0.00944  -0.0297  0.2666  1.0000
   9.500   1.3505   0.01642   0.00939  -0.0200  0.2191  1.0000
  10.000   1.1747   0.02809   0.02037   0.0006  0.0682  1.0000