XFOIL         Version 6.94
  
 Calculated polar for: gradus2                                         
  
 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
 ------- -------- --------- --------- -------- ------- -------
  -2.500  -0.2236   0.03139   0.02117  -0.0014  0.9999  0.4303
  -2.000  -0.2010   0.03050   0.02031   0.0082  0.9999  0.6188
  -1.000   0.0480   0.02905   0.01921  -0.0222  0.9999  1.0001
  -0.500   0.0992   0.02991   0.01981  -0.0226  0.9999  1.0001
   0.000   0.1493   0.03084   0.02070  -0.0227  0.9999  1.0001
   0.500   0.4947   0.02526   0.01316  -0.0713  0.5186  1.0001
   1.000   0.5596   0.02689   0.01398  -0.0730  0.4708  1.0001
   1.500   0.6308   0.02837   0.01496  -0.0761  0.4435  1.0001
   2.000   0.7060   0.02990   0.01627  -0.0800  0.4246  1.0001
   2.500   0.7783   0.03164   0.01801  -0.0834  0.4133  1.0001
   3.000   0.8409   0.03379   0.02031  -0.0850  0.4065  1.0001
   3.500   0.8937   0.03626   0.02312  -0.0850  0.4003  1.0001
   4.000   0.9438   0.03914   0.02604  -0.0844  0.3906  1.0001
   4.500   0.9815   0.04236   0.02981  -0.0821  0.3839  1.0001
   5.000   1.0158   0.04620   0.03409  -0.0796  0.3807  1.0001