XFOIL         Version 6.94
  
 Calculated polar for: gradus3                                         
  
 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  -0.2118   0.02616   0.01694  -0.0026  0.9886  0.1957
  -1.000   0.1408   0.02177   0.01084  -0.0262  0.4005  0.5877
  -0.500   0.2255   0.02205   0.01066  -0.0324  0.3452  0.6152
   0.000   0.3235   0.02222   0.01070  -0.0417  0.3364  0.6362
   0.500   0.4310   0.02248   0.01100  -0.0532  0.3268  0.6589
   1.000   0.5217   0.02312   0.01178  -0.0610  0.3190  0.6829
   1.500   0.6100   0.02382   0.01298  -0.0686  0.3096  0.7214
   2.000   0.7409   0.02622   0.01582  -0.0853  0.2962  0.9856
   2.500   0.8220   0.02825   0.01792  -0.0915  0.2893  1.0001
   3.000   0.8711   0.03024   0.02005  -0.0906  0.2860  1.0001
   3.500   0.9165   0.03247   0.02245  -0.0890  0.2822  1.0001
   4.000   0.9580   0.03506   0.02532  -0.0869  0.2793  1.0001
   4.500   0.9950   0.03805   0.02855  -0.0841  0.2765  1.0001
   5.000   1.0268   0.04154   0.03230  -0.0806  0.2739  1.0001