XFOIL         Version 6.94
  
 Calculated polar for: WORTMANN FX 77-W-258 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
 ------- -------- --------- --------- -------- ------- -------
   0.000   0.3588   0.02561   0.01603  -0.0439  0.4338  0.0621
   0.500   0.4185   0.02561   0.01611  -0.0453  0.4309  0.0695
   1.000   0.4772   0.02576   0.01643  -0.0469  0.4274  0.1001
   1.500   0.5351   0.02607   0.01696  -0.0485  0.4239  0.1531
   2.000   0.5991   0.02514   0.01777  -0.0529  0.4204  0.6011
   4.000   0.8225   0.02799   0.02075  -0.0518  0.4067  0.6924
   4.500   0.8637   0.02846   0.02145  -0.0485  0.4014  0.7105
   5.000   0.9327   0.02667   0.01954  -0.0497  0.3943  0.7214
   5.500   1.0019   0.02419   0.01687  -0.0515  0.3857  0.7266
   6.000   1.0666   0.02293   0.01544  -0.0532  0.3790  0.7290
   6.500   1.1229   0.02294   0.01534  -0.0542  0.3737  0.7318
   7.000   1.1748   0.02320   0.01568  -0.0548  0.3705  0.7358
   7.500   1.2256   0.02346   0.01605  -0.0553  0.3668  0.7395
   8.000   1.2750   0.02380   0.01650  -0.0559  0.3609  0.7420
   8.500   1.3224   0.02408   0.01680  -0.0562  0.3535  0.7443
   9.000   1.3636   0.02394   0.01648  -0.0552  0.3406  0.7465
   9.500   1.3502   0.02736   0.01967  -0.0513  0.3065  0.7484