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 =     0.080 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
  -2.500  -0.0122   0.02061   0.01247  -0.0270  0.8295  0.4593
  -2.000   0.0500   0.02043   0.01184  -0.0252  0.7580  0.5099
  -1.500   0.1059   0.02028   0.01078  -0.0223  0.6121  0.5530
  -1.000   0.1492   0.02024   0.00973  -0.0188  0.4273  0.5926
  -0.500   0.2191   0.02050   0.00911  -0.0218  0.3524  0.6167
   0.000   0.2992   0.02068   0.00914  -0.0271  0.3394  0.6357
   0.500   0.3877   0.02085   0.00936  -0.0343  0.3304  0.6565
   1.000   0.4696   0.02130   0.00993  -0.0401  0.3224  0.6785
   1.500   0.5512   0.02192   0.01094  -0.0460  0.3141  0.7112
   2.000   0.6814   0.02386   0.01356  -0.0624  0.3006  0.9804
   2.500   0.7618   0.02584   0.01559  -0.0683  0.2915  1.0001
   3.000   0.8134   0.02767   0.01755  -0.0679  0.2877  1.0001
   3.500   0.8618   0.02978   0.01983  -0.0670  0.2838  1.0001
   4.000   0.9064   0.03224   0.02259  -0.0657  0.2806  1.0001
   4.500   0.9468   0.03513   0.02574  -0.0639  0.2777  1.0001
   5.000   0.9820   0.03856   0.02945  -0.0615  0.2749  1.0001