XFOIL         Version 6.94
  
 Calculated polar for: gradus32                                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.020 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
  -3.000  -0.3165   0.04768   0.03682   0.0148  0.9999  0.4775
  -2.500  -0.2724   0.03909   0.02772   0.0180  0.9999  0.6700
  -1.500  -0.0030   0.03618   0.02342  -0.0200  0.9999  1.0001
  -1.000   0.0373   0.03755   0.02423  -0.0204  0.9999  1.0001
  -0.500   0.0771   0.03918   0.02540  -0.0207  0.9999  1.0001
   0.000   0.1143   0.04118   0.02719  -0.0209  0.9999  1.0001
   0.500   0.1439   0.04405   0.03009  -0.0215  0.9999  1.0001
   1.000   0.5098   0.04486   0.03098  -0.0767  0.7292  1.0001
   1.500   0.5285   0.04997   0.03582  -0.0747  0.6749  1.0001
   2.000   0.6165   0.05296   0.03838  -0.0787  0.6363  1.0001
   2.500   0.6024   0.06030   0.04566  -0.0755  0.6211  1.0001
   3.000   0.5876   0.06771   0.05291  -0.0725  0.6071  1.0001
   3.500   0.5749   0.07503   0.06006  -0.0699  0.6007  1.0001
   4.000   0.5706   0.08248   0.06736  -0.0691  0.6030  1.0001
   4.500   0.5734   0.09004   0.07487  -0.0693  0.6102  1.0001
   5.000   0.5873   0.09830   0.08302  -0.0707  0.6219  1.0001