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 =     0.100 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
  -3.000  -0.0261   0.01716   0.00924  -0.0361  0.8274  0.3626
  -2.500   0.0315   0.01758   0.00915  -0.0332  0.7238  0.4427
  -2.000   0.0741   0.01829   0.00917  -0.0283  0.5947  0.4795
  -1.500   0.1147   0.01931   0.00887  -0.0242  0.3996  0.5085
  -1.000   0.1621   0.01970   0.00901  -0.0216  0.3388  0.5401
  -0.500   0.2156   0.01966   0.00899  -0.0208  0.3258  0.5688
   0.000   0.2742   0.01988   0.00913  -0.0213  0.3144  0.5864
   0.500   0.3448   0.02028   0.00945  -0.0245  0.3043  0.6022
   1.000   0.4223   0.02089   0.01003  -0.0295  0.2942  0.6203
   1.500   0.4948   0.02182   0.01089  -0.0335  0.2828  0.6358
   2.000   0.5681   0.02299   0.01210  -0.0378  0.2716  0.6534
   2.500   0.6386   0.02439   0.01379  -0.0416  0.2648  0.6745
   3.000   0.6997   0.02606   0.01601  -0.0435  0.2611  0.7146
   4.000   0.8799   0.03540   0.02662  -0.0627  0.2534  0.9975
   4.500   0.9162   0.04150   0.03324  -0.0624  0.2510  1.0001
   5.000   0.9523   0.04388   0.03578  -0.0599  0.2487  1.0001