XFOIL         Version 6.94
  
 Calculated polar for: S2055                                           
  
 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   0.2899   0.00797   0.00359  -0.0618  0.9228  0.9921
   0.500   0.3715   0.00755   0.00312  -0.0671  0.9051  1.0000
   1.000   0.4174   0.00732   0.00284  -0.0650  0.8771  1.0000
   1.500   0.4620   0.00719   0.00265  -0.0624  0.8464  1.0000
   2.000   0.5057   0.00717   0.00255  -0.0596  0.8120  1.0000
   2.500   0.5485   0.00724   0.00257  -0.0566  0.7726  1.0000
   3.000   0.5898   0.00740   0.00263  -0.0533  0.7200  1.0000
   3.500   0.6266   0.00782   0.00269  -0.0490  0.6184  1.0000
   4.000   0.6566   0.00888   0.00305  -0.0438  0.4582  1.0000
   4.500   0.6930   0.00997   0.00363  -0.0403  0.3434  1.0000
   5.500   0.7796   0.01179   0.00497  -0.0362  0.2005  1.0000
   6.000   0.8218   0.01306   0.00584  -0.0342  0.1061  1.0000
   6.500   0.8604   0.01498   0.00747  -0.0315  0.0495  1.0000
   7.000   0.8996   0.01691   0.00953  -0.0286  0.0372  1.0000
   7.500   0.9355   0.01972   0.01248  -0.0254  0.0307  1.0000
   8.000   0.9780   0.02192   0.01504  -0.0232  0.0264  1.0000
   8.500   1.0163   0.02424   0.01755  -0.0209  0.0203  1.0000
   9.000   1.0482   0.02932   0.02329  -0.0174  0.0168  1.0000
   9.500   1.0750   0.03322   0.02768  -0.0137  0.0142  1.0000
  10.000   1.0794   0.03885   0.03377  -0.0089  0.0117  1.0000
  11.000   1.0245   0.05253   0.04860   0.0043  0.0114  1.0000
  12.000   0.9574   0.07134   0.06813   0.0002  0.0116  1.0000
  12.500   0.9192   0.08714   0.08423  -0.0114  0.0116  1.0000