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 =     0.012 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
   0.000   0.2819   0.04399   0.02684  -0.0138  0.9994  1.0006
   0.250   0.2993   0.04502   0.02791  -0.0128  0.9994  1.0006
   0.500   0.3169   0.04610   0.02890  -0.0124  0.9994  1.0006
   0.750   0.3343   0.04727   0.02999  -0.0122  0.9994  1.0006
   1.000   0.3513   0.04854   0.03123  -0.0122  0.9994  1.0006
   1.250   0.3676   0.04996   0.03266  -0.0124  0.9994  1.0006
   1.500   0.3829   0.05156   0.03429  -0.0127  0.9994  1.0006
   1.750   0.3968   0.05339   0.03623  -0.0132  0.9994  1.0006
   2.000   0.4087   0.05556   0.03855  -0.0140  0.9994  1.0006
   2.250   0.4177   0.05821   0.04137  -0.0152  0.9994  1.0006
   2.500   0.4231   0.06146   0.04480  -0.0169  0.9994  1.0006
   2.750   0.4261   0.06522   0.04872  -0.0191  0.9994  1.0006
   3.000   0.4290   0.06915   0.05276  -0.0215  0.9994  1.0006
   3.250   0.4328   0.07302   0.05672  -0.0238  0.9994  1.0006
   3.500   0.4376   0.07678   0.06055  -0.0260  0.9994  1.0006
   3.750   0.4433   0.08045   0.06427  -0.0281  0.9994  1.0006
   4.000   0.4497   0.08406   0.06794  -0.0300  0.9994  1.0006
   4.250   0.4565   0.08762   0.07156  -0.0319  0.9994  1.0006
   4.500   0.4638   0.09116   0.07515  -0.0338  0.9994  1.0006
   4.750   0.4714   0.09468   0.07872  -0.0356  0.9994  1.0006
   5.000   0.4936   0.09891   0.08305  -0.0408  0.9874  1.0006