XFOIL         Version 6.94
  
 Calculated polar for: WORTMANN FX 2 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   0.2431   0.02389   0.01422  -0.0816  0.0746  0.6380
   1.000   0.2940   0.02427   0.01433  -0.0828  0.0602  0.6043
   1.500   0.3357   0.02542   0.01536  -0.0811  0.0344  0.6449
   2.000   0.3778   0.02655   0.01652  -0.0797  0.0337  0.6652
   4.000   0.5379   0.03034   0.01806  -0.0727  0.0185  0.0373
   4.500   0.5945   0.03053   0.01881  -0.0744  0.0875  0.1667
   5.000   0.6648   0.03025   0.01972  -0.0808  0.0812  0.5642
   7.000   0.8133   0.03561   0.02563  -0.0738  0.0627  0.7000
   7.500   0.8381   0.03783   0.02751  -0.0714  0.0163  0.6981
   8.500   1.0663   0.03106   0.02347  -0.0886  0.3674  0.6728
   9.000   1.0961   0.03273   0.02490  -0.0863  0.3408  0.6265
   9.500   1.0442   0.03985   0.03102  -0.0741  0.1548  0.7001
  10.000   1.0723   0.04205   0.03299  -0.0727  0.1170  0.6798