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 =     0.010 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
  -2.500  -0.0632   0.04422   0.02675  -0.0239  0.9999  1.0001
  -2.000  -0.0295   0.04459   0.02609  -0.0235  0.9999  1.0001
  -1.500   0.0085   0.04541   0.02602  -0.0232  0.9999  1.0001
  -1.000   0.0474   0.04652   0.02644  -0.0229  0.9999  1.0001
  -0.500   0.0858   0.04792   0.02720  -0.0225  0.9999  1.0001
   0.000   0.1224   0.04961   0.02851  -0.0222  0.9999  1.0001
   0.500   0.1561   0.05170   0.03040  -0.0219  0.9999  1.0001
   1.000   0.1842   0.05445   0.03313  -0.0219  0.9999  1.0001
   1.500   0.1997   0.05870   0.03752  -0.0227  0.9999  1.0001
   2.000   0.1962   0.06543   0.04431  -0.0253  0.9999  1.0001
   2.500   0.2024   0.07162   0.05030  -0.0279  0.9999  1.0001
   3.000   0.2169   0.07713   0.05556  -0.0301  0.9999  1.0001
   3.500   0.2349   0.08240   0.06055  -0.0320  0.9999  1.0001
   4.000   0.2548   0.08757   0.06547  -0.0337  0.9999  1.0001
   4.500   0.2756   0.09272   0.07039  -0.0353  0.9999  1.0001
   5.000   0.2968   0.09787   0.07534  -0.0368  0.9999  1.0001