XFOIL         Version 6.94
  
 Calculated polar for: AG18                                            
  
 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   0.2677   0.00592   0.00175  -0.0580  0.9413  1.0000
   0.500   0.3251   0.00597   0.00162  -0.0573  0.8887  1.0000
   1.000   0.3758   0.00617   0.00157  -0.0551  0.8272  1.0000
   1.500   0.4271   0.00649   0.00159  -0.0533  0.7597  1.0000
   2.000   0.4792   0.00690   0.00169  -0.0519  0.6850  1.0000
   2.500   0.5316   0.00741   0.00185  -0.0507  0.5989  1.0000
   3.000   0.5839   0.00805   0.00213  -0.0498  0.5029  1.0000
   3.500   0.6364   0.00880   0.00250  -0.0491  0.4100  1.0000
   4.000   0.6892   0.00959   0.00299  -0.0486  0.3284  1.0000
   4.500   0.7420   0.01041   0.00360  -0.0481  0.2576  1.0000
   5.000   0.7943   0.01133   0.00431  -0.0476  0.1935  1.0000
   5.500   0.8462   0.01236   0.00521  -0.0471  0.1373  1.0000
   6.000   0.8975   0.01354   0.00630  -0.0465  0.0926  1.0000
   6.500   0.9474   0.01505   0.00779  -0.0456  0.0591  1.0000
   7.000   0.9959   0.01691   0.00973  -0.0445  0.0349  1.0000
   7.500   1.0421   0.01928   0.01230  -0.0430  0.0213  1.0000
   8.000   1.0834   0.02293   0.01631  -0.0408  0.0153  1.0000
   8.500   1.1232   0.02689   0.02074  -0.0386  0.0129  1.0000
   9.000   1.1518   0.03351   0.02809  -0.0358  0.0121  1.0000
  10.000   1.1556   0.05015   0.04651  -0.0304  0.0105  1.0000
  10.500   1.1227   0.05915   0.05602  -0.0303  0.0105  1.0000
  11.000   1.0800   0.07485   0.07207  -0.0426  0.0110  1.0000