XFOIL         Version 6.94
  
 Calculated polar for: Dayton-Wright T-1                               
  
 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   0.6601   0.00915   0.00292  -0.0914  0.5850  0.3960
   0.500   0.7039   0.00880   0.00298  -0.0895  0.5565  0.5969
   1.000   0.8423   0.00895   0.00362  -0.1074  0.4946  0.9993
   1.500   0.8884   0.00925   0.00377  -0.1061  0.4683  1.0000
   2.000   0.9158   0.01003   0.00409  -0.1010  0.3970  1.0000
   2.500   0.9537   0.01050   0.00435  -0.0980  0.3705  1.0000
   3.000   0.9792   0.01134   0.00481  -0.0926  0.3244  1.0000
   4.000   1.0584   0.01234   0.00578  -0.0875  0.2952  1.0000
   4.500   1.1022   0.01264   0.00613  -0.0858  0.2940  1.0000
   5.000   1.1466   0.01293   0.00647  -0.0844  0.2917  1.0000
   5.500   1.1851   0.01327   0.00673  -0.0820  0.2779  1.0000
   6.000   1.2189   0.01403   0.00729  -0.0790  0.2551  1.0000
   6.500   1.2505   0.01497   0.00809  -0.0757  0.2320  1.0000
   7.000   1.2831   0.01595   0.00905  -0.0729  0.2071  1.0000
   8.000   1.2625   0.02292   0.01477  -0.0568  0.0488  1.0000
   8.500   1.2757   0.02572   0.01728  -0.0527  0.0182  1.0000
   9.000   1.3014   0.02761   0.01924  -0.0504  0.0133  1.0000
   9.500   1.3125   0.03046   0.02236  -0.0470  0.0119  1.0000
  10.000   1.3296   0.03329   0.02542  -0.0445  0.0117  1.0000
  11.500   1.3227   0.04923   0.04223  -0.0375  0.0117  1.0000