XFOIL         Version 6.94
  
 Calculated polar for: AG19                                            
  
 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   0.2716   0.00591   0.00176  -0.0582  0.9528  1.0000
   0.500   0.3339   0.00593   0.00161  -0.0585  0.9034  1.0000
   1.000   0.3849   0.00610   0.00155  -0.0563  0.8421  1.0000
   1.500   0.4356   0.00641   0.00155  -0.0543  0.7735  1.0000
   2.000   0.4872   0.00682   0.00165  -0.0527  0.6953  1.0000
   2.500   0.5391   0.00736   0.00180  -0.0514  0.6007  1.0000
   3.000   0.5909   0.00807   0.00205  -0.0504  0.4913  1.0000
   3.500   0.6432   0.00889   0.00248  -0.0497  0.3899  1.0000
   4.000   0.6959   0.00970   0.00299  -0.0492  0.3088  1.0000
   4.500   0.7486   0.01053   0.00362  -0.0488  0.2400  1.0000
   5.000   0.8010   0.01147   0.00435  -0.0483  0.1785  1.0000
   5.500   0.8528   0.01254   0.00528  -0.0477  0.1271  1.0000
   6.000   0.9041   0.01373   0.00641  -0.0471  0.0888  1.0000
   6.500   0.9543   0.01517   0.00787  -0.0462  0.0596  1.0000
   7.000   1.0027   0.01704   0.00986  -0.0451  0.0365  1.0000
   8.000   1.0916   0.02291   0.01631  -0.0416  0.0157  1.0000
   8.500   1.1317   0.02688   0.02079  -0.0395  0.0130  1.0000
   9.000   1.1594   0.03374   0.02839  -0.0367  0.0120  1.0000
   9.500   1.1674   0.04255   0.03825  -0.0338  0.0109  1.0000
  10.000   1.1637   0.05046   0.04692  -0.0316  0.0103  1.0000
  10.500   1.1289   0.05993   0.05690  -0.0321  0.0104  1.0000
  11.000   1.0902   0.07602   0.07335  -0.0458  0.0108  1.0000