XFOIL         Version 6.94
  
 Calculated polar for: S7055 (10.5%) Flat-Bottomed                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.080     Re =     0.450 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
   0.000   0.4224   0.00665   0.00215  -0.0812  0.7053  0.9958
   0.500   0.4838   0.00670   0.00204  -0.0826  0.6848  1.0000
   1.000   0.5315   0.00680   0.00200  -0.0809  0.6635  1.0000
   1.500   0.5796   0.00696   0.00200  -0.0793  0.6428  1.0000
   2.000   0.6282   0.00713   0.00207  -0.0778  0.6215  1.0000
   2.500   0.6769   0.00733   0.00218  -0.0764  0.5989  1.0000
   3.000   0.7252   0.00759   0.00231  -0.0749  0.5749  1.0000
   3.500   0.7739   0.00784   0.00251  -0.0734  0.5505  1.0000
   4.000   0.8220   0.00816   0.00274  -0.0719  0.5264  1.0000
   4.500   0.8701   0.00849   0.00304  -0.0704  0.4998  1.0000
   5.000   0.9175   0.00886   0.00336  -0.0689  0.4720  1.0000
   5.500   0.9642   0.00930   0.00375  -0.0672  0.4439  1.0000
   6.000   1.0101   0.00979   0.00418  -0.0654  0.4131  1.0000
   6.500   1.0553   0.01033   0.00468  -0.0636  0.3797  1.0000
   7.000   1.0993   0.01095   0.00526  -0.0617  0.3447  1.0000
   7.500   1.1401   0.01174   0.00594  -0.0593  0.3025  1.0000
   8.000   1.1763   0.01278   0.00676  -0.0563  0.2449  1.0000
   8.500   1.2063   0.01416   0.00784  -0.0524  0.1807  1.0000
   9.000   1.2328   0.01564   0.00906  -0.0481  0.1290  1.0000
   9.500   1.2488   0.01729   0.01047  -0.0421  0.0821  1.0000
  10.000   1.2589   0.01937   0.01233  -0.0358  0.0414  1.0000
  10.500   1.2540   0.02273   0.01550  -0.0285  0.0110  1.0000