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 =     0.040 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
  -2.000  -0.2157   0.03413   0.02403   0.0110  0.9999  0.5349
  -1.500  -0.1570   0.03249   0.02202   0.0105  0.9999  0.6355
  -1.000   0.0395   0.03142   0.02207  -0.0194  0.9999  1.0001
  -0.500   0.1874   0.03131   0.02172  -0.0388  0.9567  1.0001
   0.000   0.4602   0.02560   0.01401  -0.0734  0.5156  1.0001
   0.500   0.5233   0.02727   0.01480  -0.0750  0.4580  1.0001
   1.000   0.6003   0.02884   0.01605  -0.0796  0.4343  1.0001
   1.500   0.6724   0.03044   0.01770  -0.0833  0.4226  1.0001
   2.000   0.7399   0.03241   0.01989  -0.0863  0.4140  1.0001
   2.500   0.7987   0.03486   0.02255  -0.0878  0.4083  1.0001
   3.000   0.8475   0.03791   0.02587  -0.0878  0.4053  1.0001
   3.500   0.8869   0.04151   0.02974  -0.0864  0.4020  1.0001
   4.000   0.9181   0.04516   0.03355  -0.0834  0.3925  1.0001
   4.500   0.9415   0.04943   0.03810  -0.0796  0.3853  1.0001
   5.000   0.9538   0.05464   0.04353  -0.0750  0.3809  1.0001