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 =     0.300 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
   0.500   0.4998   0.03348   0.02606  -0.0618  0.4177  0.5508
   1.500   0.6096   0.03500   0.02775  -0.0639  0.4126  0.5905
   2.000   0.6662   0.03574   0.02845  -0.0651  0.4105  0.6039
   2.500   0.7181   0.03712   0.02981  -0.0658  0.4077  0.6161
   3.500   0.2767   0.09317   0.08679  -0.0495  0.3738  0.5957
   5.500   0.3599   0.10850   0.10211  -0.0536  0.3465  0.6288
   6.000   0.4060   0.10949   0.10316  -0.0541  0.3448  0.6354
   6.500   0.4466   0.11061   0.10441  -0.0528  0.3431  0.6460
   7.000   0.3483   0.13129   0.12522  -0.0563  0.3240  0.6406
   7.500   0.3727   0.13486   0.12890  -0.0559  0.3213  0.6514
   8.000   0.4062   0.13757   0.13162  -0.0561  0.3190  0.6607
   8.500   0.4407   0.13947   0.13367  -0.0556  0.3173  0.6698
   9.000   0.4767   0.14128   0.13555  -0.0550  0.3158  0.6782
   9.500   0.5171   0.14272   0.13700  -0.0551  0.3140  0.6871