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 =     0.045 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
   1.500   0.6574   0.03128   0.02170  -0.0518  0.8239  0.4428
   1.750   0.6725   0.03087   0.02123  -0.0447  0.7532  0.4370
   2.000   0.6855   0.03062   0.02061  -0.0375  0.6620  0.4297
   2.250   0.7037   0.03100   0.02038  -0.0331  0.5747  0.4239
   2.500   0.7260   0.03174   0.02058  -0.0310  0.5126  0.4207
   2.750   0.7504   0.03274   0.02116  -0.0300  0.4681  0.4186
   3.000   0.7759   0.03391   0.02200  -0.0294  0.4358  0.4173
   3.250   0.8024   0.03518   0.02311  -0.0293  0.4076  0.4161
   3.500   0.8287   0.03661   0.02431  -0.0291  0.3854  0.4146
   3.750   0.8561   0.03822   0.02591  -0.0292  0.3679  0.4127
   4.000   0.8831   0.03995   0.02763  -0.0295  0.3511  0.4107
   4.250   0.9097   0.04178   0.02948  -0.0298  0.3345  0.4089
   4.500   0.9363   0.04379   0.03166  -0.0303  0.3204  0.4072
   4.750   0.9629   0.04601   0.03396  -0.0307  0.3102  0.4060
   5.000   0.9887   0.04811   0.03637  -0.0313  0.2994  0.4049