XFOIL         Version 6.94
  
 Calculated polar for: S2050 8.93%                                     
  
 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   0.2117   0.00750   0.00301  -0.0531  0.9068  0.8332
   0.500   0.2774   0.00734   0.00283  -0.0539  0.8689  0.8574
   1.000   0.3311   0.00737   0.00276  -0.0523  0.8181  0.8793
   1.500   0.3803   0.00750   0.00275  -0.0501  0.7657  0.9002
   2.000   0.4266   0.00762   0.00274  -0.0474  0.7129  0.9217
   2.500   0.4731   0.00775   0.00275  -0.0447  0.6570  0.9501
   3.000   0.5375   0.00801   0.00281  -0.0463  0.5883  0.9802
   3.500   0.5980   0.00849   0.00304  -0.0479  0.5150  1.0000
   4.000   0.6503   0.00915   0.00337  -0.0477  0.4341  1.0000
   4.500   0.7022   0.00989   0.00385  -0.0473  0.3563  1.0000
   5.000   0.7522   0.01082   0.00442  -0.0466  0.2687  1.0000
   5.500   0.8012   0.01192   0.00517  -0.0458  0.1810  1.0000
   6.500   0.8944   0.01493   0.00752  -0.0434  0.0497  1.0000
   8.000   1.0207   0.02170   0.01474  -0.0367  0.0260  1.0000
   8.500   1.0629   0.02451   0.01784  -0.0346  0.0242  1.0000
   9.000   1.1027   0.02801   0.02172  -0.0325  0.0231  1.0000
   9.500   1.1371   0.03200   0.02610  -0.0300  0.0218  1.0000
  10.000   1.1547   0.03891   0.03358  -0.0266  0.0206  1.0000
  10.500   1.1551   0.04633   0.04169  -0.0220  0.0204  1.0000
  11.000   1.1402   0.05239   0.04826  -0.0164  0.0205  1.0000
  11.500   1.1116   0.05860   0.05488  -0.0124  0.0207  1.0000
  12.000   1.0784   0.06692   0.06360  -0.0139  0.0210  1.0000