XFOIL         Version 6.94
  
 Calculated polar for: FX 80-080                                       
  
 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   0.2946   0.00838   0.00384  -0.0728  0.8943  0.9497
   0.500   0.3657   0.00834   0.00375  -0.0761  0.8861  0.9634
   1.000   0.4405   0.00828   0.00368  -0.0802  0.8745  0.9736
   1.500   0.5155   0.00816   0.00355  -0.0842  0.8583  0.9826
   2.500   0.6379   0.00789   0.00331  -0.0862  0.8089  1.0000
   3.000   0.6775   0.00784   0.00328  -0.0827  0.7777  1.0000
   3.500   0.7223   0.00784   0.00332  -0.0800  0.7368  1.0000
   4.000   0.7649   0.00802   0.00340  -0.0767  0.6526  1.0000
   4.500   0.7749   0.01036   0.00409  -0.0677  0.3285  1.0000
   5.000   0.8017   0.01267   0.00530  -0.0631  0.1173  1.0000
   5.500   0.8397   0.01436   0.00670  -0.0602  0.0563  1.0000
   6.000   0.8769   0.01627   0.00862  -0.0568  0.0374  1.0000
   6.500   0.9141   0.01865   0.01107  -0.0536  0.0299  1.0000
   7.000   0.9562   0.02105   0.01366  -0.0514  0.0221  1.0000
   7.500   0.9986   0.02399   0.01687  -0.0493  0.0151  1.0000
   8.000   1.0402   0.02941   0.02305  -0.0464  0.0137  1.0000
   8.500   1.0634   0.03684   0.03143  -0.0412  0.0135  1.0000
   9.000   1.0681   0.04457   0.04005  -0.0345  0.0129  1.0000
   9.500   1.0509   0.05313   0.04930  -0.0270  0.0132  1.0000
  10.000   1.0153   0.06025   0.05682  -0.0193  0.0139  1.0000
  10.500   0.9728   0.06872   0.06559  -0.0161  0.0141  1.0000