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 =     0.022 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
   1.000   0.3633   0.04201   0.03022  -0.0154  0.9994  1.0006
   1.250   0.3795   0.04357   0.03181  -0.0158  0.9994  1.0006
   1.500   0.3938   0.04544   0.03379  -0.0164  0.9994  1.0006
   1.750   0.4048   0.04784   0.03638  -0.0176  0.9994  1.0006
   2.000   0.4091   0.05139   0.04016  -0.0197  0.9994  1.0006
   2.250   0.6895   0.04987   0.03947  -0.0653  0.7982  1.0006
   2.500   0.7337   0.05018   0.03999  -0.0648  0.7301  1.0006
   2.750   0.7636   0.05103   0.04087  -0.0627  0.6814  1.0006
   3.000   0.7895   0.05216   0.04204  -0.0606  0.6426  1.0006
   3.250   0.8132   0.05378   0.04369  -0.0590  0.6116  1.0006
   3.500   0.8403   0.05457   0.04448  -0.0565  0.5818  1.0006
   3.750   0.8572   0.05759   0.04761  -0.0567  0.5579  1.0006
   4.000   0.8748   0.06068   0.05083  -0.0568  0.5383  1.0006
   4.250   0.8912   0.06359   0.05391  -0.0563  0.5182  1.0006
   4.500   0.9052   0.06700   0.05743  -0.0562  0.5013  1.0006
   4.750   0.9252   0.07030   0.06082  -0.0564  0.4902  1.0006
   5.000   0.9115   0.07790   0.06859  -0.0592  0.4872  1.0006