XFOIL         Version 6.94
  
 Calculated polar for: fc20. 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
 ------- -------- --------- --------- -------- ------- -------
  -1.500   0.1514   0.05263   0.04040  -0.0637  0.4147  0.4461
  -0.500   0.3803   0.05090   0.03759  -0.0800  0.4105  1.0001
   0.000   0.4544   0.05332   0.03939  -0.0837  0.4106  1.0001
   0.500   0.5212   0.05617   0.04189  -0.0866  0.4125  1.0001
   1.000   0.5821   0.05954   0.04509  -0.0891  0.4178  1.0001
   1.500   0.6385   0.06345   0.04889  -0.0912  0.4268  1.0001
   2.000   0.6776   0.06781   0.05347  -0.0920  0.4428  1.0001
   2.500   0.6984   0.07318   0.05914  -0.0914  0.4625  1.0001
   3.000   0.6945   0.08039   0.06659  -0.0895  0.4880  1.0001
   3.500   0.6028   0.09183   0.07846  -0.0821  0.5312  1.0001