XFOIL         Version 6.94
  
 Calculated polar for: nacd632                                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.026 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
   1.000   0.3664   0.04067   0.03012  -0.0165  0.9994  1.0006
   1.250   0.3824   0.04228   0.03178  -0.0169  0.9994  1.0006
   1.500   0.3961   0.04426   0.03389  -0.0176  0.9994  1.0006
   1.750   0.4050   0.04705   0.03689  -0.0191  0.9994  1.0006
   2.000   0.6902   0.04173   0.03252  -0.0613  0.7992  1.0006
   2.250   0.7249   0.04140   0.03226  -0.0574  0.7224  1.0006
   2.500   0.7487   0.04160   0.03239  -0.0530  0.6677  1.0006
   2.750   0.7708   0.04223   0.03295  -0.0496  0.6231  1.0006
   3.000   0.7938   0.04319   0.03385  -0.0473  0.5872  1.0006
   3.250   0.8165   0.04420   0.03480  -0.0451  0.5547  1.0006
   3.500   0.8406   0.04521   0.03571  -0.0431  0.5281  1.0006
   3.750   0.8643   0.04731   0.03790  -0.0431  0.5038  1.0006
   4.000   0.8874   0.04913   0.03984  -0.0424  0.4804  1.0006
   4.250   0.9106   0.05138   0.04217  -0.0423  0.4613  1.0006
   4.500   0.9323   0.05475   0.04574  -0.0434  0.4478  1.0006
   4.750   0.9539   0.05759   0.04868  -0.0435  0.4338  1.0006
   5.000   0.9760   0.06039   0.05150  -0.0433  0.4183  0.7748