XFOIL         Version 6.94
  
 Calculated polar for: fc55. 7.11.10.53.57. 7. 7.12.%                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.020 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
  -3.000  -0.1633   0.05895   0.05009  -0.0134  0.4351  0.3015
  -2.500  -0.0933   0.05450   0.04405  -0.0164  0.4129  0.3140
  -2.000  -0.0188   0.05081   0.03930  -0.0185  0.3998  0.3467
  -1.500   0.0570   0.04801   0.03590  -0.0199  0.3913  0.4080
  -1.000   0.1241   0.04440   0.03360  -0.0188  0.3871  0.5713
  -0.500   0.2415   0.04451   0.03240  -0.0268  0.3846  1.0001
   0.000   0.3046   0.04740   0.03462  -0.0286  0.3855  1.0001
   0.500   0.3659   0.05094   0.03772  -0.0311  0.3884  1.0001
   1.000   0.4266   0.05625   0.04325  -0.0371  0.3967  1.0001
   1.500   0.4800   0.06268   0.04958  -0.0428  0.4070  1.0001
   2.000   0.5151   0.07245   0.05956  -0.0520  0.4261  1.0001
   2.500   0.4994   0.08596   0.07334  -0.0618  0.4591  1.0001
   3.000   0.4680   0.09777   0.08512  -0.0668  0.5018  1.0001