XFOIL         Version 6.94
  
 Calculated polar for: Glenn Martin 4                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.080     Re =     0.300 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
   1.500   0.5655   0.01596   0.00695  -0.0718  0.4610  0.0750
   2.000   0.6000   0.01665   0.00725  -0.0688  0.3993  0.0762
   2.500   0.6432   0.01698   0.00747  -0.0675  0.3816  0.0819
   3.000   0.6732   0.01807   0.00806  -0.0639  0.3278  0.0892
   4.000   0.7898   0.01790   0.01060  -0.0681  0.3235  0.9551
   4.500   0.8999   0.01918   0.01196  -0.0815  0.3207  1.0000
   5.000   0.9457   0.01990   0.01276  -0.0811  0.3203  1.0000
   5.500   0.9879   0.02075   0.01370  -0.0800  0.3202  1.0000
   6.000   1.0259   0.02174   0.01479  -0.0783  0.3201  1.0000
   6.500   1.0597   0.02287   0.01605  -0.0758  0.3201  1.0000
   7.000   1.0891   0.02417   0.01749  -0.0727  0.3199  1.0000
   7.500   1.1134   0.02569   0.01916  -0.0689  0.3194  1.0000
   8.000   1.1267   0.02787   0.02152  -0.0636  0.3147  1.0000
   8.500   1.1266   0.03065   0.02453  -0.0567  0.3114  1.0000
   9.000   1.1014   0.03468   0.02883  -0.0470  0.3087  1.0000
   9.500   1.0490   0.04194   0.03646  -0.0367  0.3048  1.0000