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 =     0.040 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
   1.500   0.6569   0.03323   0.02358  -0.0559  0.8523  0.4781
   1.750   0.6790   0.03266   0.02296  -0.0495  0.7742  0.4702
   2.000   0.6923   0.03235   0.02229  -0.0415  0.6896  0.4642
   2.250   0.7094   0.03257   0.02206  -0.0364  0.6063  0.4590
   2.500   0.7307   0.03314   0.02213  -0.0335  0.5471  0.4543
   2.750   0.7547   0.03408   0.02267  -0.0321  0.4998  0.4495
   3.000   0.7802   0.03523   0.02346  -0.0312  0.4645  0.4452
   3.250   0.8058   0.03648   0.02437  -0.0306  0.4369  0.4419
   3.500   0.8323   0.03785   0.02571  -0.0306  0.4107  0.4394
   3.750   0.8592   0.03942   0.02729  -0.0306  0.3909  0.4370
   4.000   0.8863   0.04120   0.02909  -0.0308  0.3742  0.4347
   4.250   0.9126   0.04308   0.03099  -0.0311  0.3576  0.4325
   4.500   0.9384   0.04512   0.03309  -0.0313  0.3417  0.4304
   4.750   0.9646   0.04740   0.03534  -0.0315  0.3303  0.4288
   5.000   0.9901   0.05004   0.03848  -0.0325  0.3200  0.4279