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 =     0.035 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
   1.000   0.3715   0.03871   0.03009  -0.0185  0.9994  1.0006
   1.250   0.4278   0.03937   0.03089  -0.0263  0.9808  1.0006
   1.500   0.6125   0.03697   0.02760  -0.0544  0.8961  0.5545
   1.750   0.6831   0.03500   0.02534  -0.0552  0.8014  0.5196
   2.000   0.7006   0.03470   0.02476  -0.0475  0.7129  0.5111
   2.250   0.7174   0.03477   0.02447  -0.0415  0.6397  0.5054
   2.500   0.7381   0.03525   0.02450  -0.0378  0.5834  0.5007
   2.750   0.7612   0.03607   0.02495  -0.0358  0.5371  0.4966
   3.000   0.7854   0.03703   0.02563  -0.0343  0.4995  0.4919
   3.250   0.8109   0.03822   0.02655  -0.0334  0.4706  0.4865
   3.500   0.8370   0.03969   0.02786  -0.0331  0.4435  0.4813
   3.750   0.8628   0.04110   0.02913  -0.0326  0.4208  0.4765
   4.000   0.8898   0.04293   0.03097  -0.0327  0.4033  0.4718
   4.250   0.9163   0.04498   0.03311  -0.0331  0.3867  0.4681
   4.500   0.9418   0.04709   0.03526  -0.0333  0.3699  0.4653
   4.750   0.9666   0.04956   0.03791  -0.0338  0.3551  0.4636
   5.000   0.9917   0.05243   0.04096  -0.0344  0.3454  0.4623