XFOIL         Version 6.94
  
 Calculated polar for: WORTMANN FX 77-W-343 AIRFOIL                    
  
 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
 ------- -------- --------- --------- -------- ------- -------
   0.500   0.5436   0.02600   0.01697  -0.0588  0.4072  0.1206
   1.000   0.5996   0.02783   0.01917  -0.0622  0.4041  0.1913
   1.500   0.6706   0.02732   0.01900  -0.0673  0.4034  0.2783
   2.000   0.7450   0.02659   0.01878  -0.0735  0.4024  0.4295
   2.500   0.8148   0.02618   0.01875  -0.0781  0.4009  0.5164
   3.500   0.9391   0.02634   0.01931  -0.0825  0.3960  0.5973
   4.000   1.0008   0.02631   0.01932  -0.0840  0.3925  0.6202
   4.500   1.0676   0.02584   0.01873  -0.0862  0.3884  0.6292
   5.500   1.1953   0.02442   0.01705  -0.0899  0.3742  0.6425
   6.000   1.2463   0.02494   0.01765  -0.0898  0.3713  0.6516
   6.500   1.2941   0.02563   0.01843  -0.0896  0.3693  0.6591
   7.000   1.3373   0.02609   0.01898  -0.0893  0.3666  0.6653
   7.500   1.3522   0.02734   0.02038  -0.0849  0.3634  0.6682
   8.000   1.3736   0.02951   0.02270  -0.0834  0.3593  0.6705
   8.500   1.3940   0.03226   0.02554  -0.0830  0.3537  0.6730
   9.000   1.4110   0.03562   0.02894  -0.0831  0.3475  0.6756
   9.500   1.4075   0.04100   0.03437  -0.0826  0.3407  0.6782