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 =     0.030 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
   1.000   0.3689   0.03967   0.03009  -0.0174  0.9994  1.0006
   1.250   0.3846   0.04132   0.03181  -0.0178  0.9994  1.0006
   1.500   0.3992   0.04337   0.03403  -0.0190  0.9983  1.0006
   1.750   0.6458   0.03802   0.02960  -0.0568  0.8564  1.0006
   2.000   0.7010   0.03715   0.02842  -0.0548  0.7532  0.6753
   2.250   0.7255   0.03770   0.02822  -0.0496  0.6791  0.6076
   2.500   0.7467   0.03820   0.02823  -0.0452  0.6239  0.5856
   2.750   0.7696   0.03891   0.02847  -0.0420  0.5818  0.5708
   3.000   0.7931   0.03982   0.02904  -0.0398  0.5445  0.5602
   3.250   0.8176   0.04107   0.03006  -0.0386  0.5114  0.5522
   3.500   0.8430   0.04263   0.03155  -0.0381  0.4849  0.5463
   3.750   0.8681   0.04408   0.03296  -0.0374  0.4600  0.5424
   4.000   0.8935   0.04573   0.03451  -0.0369  0.4390  0.5396
   4.250   0.9196   0.04814   0.03704  -0.0375  0.4230  0.5374
   4.500   0.9442   0.05068   0.03970  -0.0380  0.4071  0.5347
   4.750   0.9671   0.05324   0.04240  -0.0382  0.3907  0.5314
   5.000   0.9894   0.05628   0.04562  -0.0388  0.3781  0.5272