XFOIL         Version 6.94
  
 Calculated polar for: AG14                                            
  
 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   0.2319   0.00586   0.00173  -0.0494  0.9764  1.0000
   0.500   0.3088   0.00583   0.00158  -0.0531  0.9253  1.0000
   1.000   0.3633   0.00599   0.00147  -0.0515  0.8397  1.0000
   1.500   0.4129   0.00643   0.00147  -0.0491  0.7424  1.0000
   2.000   0.4641   0.00699   0.00159  -0.0476  0.6438  1.0000
   2.500   0.5164   0.00760   0.00179  -0.0465  0.5490  1.0000
   3.000   0.5693   0.00825   0.00210  -0.0458  0.4622  1.0000
   3.500   0.6226   0.00891   0.00248  -0.0452  0.3827  1.0000
   4.000   0.6759   0.00963   0.00294  -0.0448  0.3091  1.0000
   4.500   0.7290   0.01043   0.00355  -0.0443  0.2392  1.0000
   5.000   0.7815   0.01137   0.00427  -0.0439  0.1745  1.0000
   5.500   0.8335   0.01248   0.00524  -0.0434  0.1216  1.0000
   6.000   0.8848   0.01376   0.00643  -0.0427  0.0824  1.0000
   6.500   0.9358   0.01509   0.00784  -0.0420  0.0526  1.0000
   8.000   1.0689   0.02496   0.01862  -0.0368  0.0146  1.0000
   8.500   1.1054   0.03075   0.02520  -0.0343  0.0136  1.0000
   9.000   1.1343   0.03673   0.03197  -0.0321  0.0121  1.0000
   9.500   1.1514   0.04324   0.03922  -0.0301  0.0109  1.0000
  10.000   1.1281   0.05450   0.05136  -0.0289  0.0112  1.0000
  10.500   1.0831   0.06783   0.06514  -0.0369  0.0116  1.0000
  11.000   1.0163   0.09740   0.09495  -0.0607  0.0142  1.0000
  11.500   0.9862   0.11485   0.11238  -0.0690  0.0155  1.0000