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 =     0.450 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
   0.000   0.4152   0.01461   0.00628  -0.0719  0.4658  0.0423
   0.500   0.4541   0.01511   0.00635  -0.0697  0.3993  0.0418
   1.000   0.5022   0.01535   0.00635  -0.0693  0.3785  0.0417
   1.500   0.5467   0.01575   0.00642  -0.0683  0.3540  0.0425
   2.000   0.5905   0.01613   0.00667  -0.0672  0.3263  0.0455
   2.500   0.6366   0.01644   0.00708  -0.0665  0.2992  0.0488
   3.000   0.6854   0.01665   0.00743  -0.0664  0.2985  0.0660
   3.500   0.7369   0.01711   0.00815  -0.0669  0.2984  0.0833
   4.000   0.7928   0.01774   0.00907  -0.0683  0.2985  0.0980
   4.500   0.8552   0.01892   0.01088  -0.0715  0.2989  0.1825
   5.000   0.9078   0.01968   0.01380  -0.0736  0.2997  0.8643
   5.500   0.8873   0.02094   0.01523  -0.0588  0.3009  0.9594
   6.000   1.0282   0.02265   0.01708  -0.0800  0.3020  1.0000
   6.500   1.0468   0.02431   0.01887  -0.0749  0.3023  1.0000
   7.000   1.0617   0.02623   0.02094  -0.0695  0.3025  1.0000
   7.500   1.0457   0.03005   0.02503  -0.0601  0.3006  1.0000