XFOIL         Version 6.94
  
 Calculated polar for: AG12                                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.080     Re =     0.450 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
   0.000   0.2281   0.00482   0.00120  -0.0483  0.8667  1.0000
   0.500   0.2793   0.00514   0.00113  -0.0465  0.7871  1.0000
   1.000   0.3322   0.00552   0.00113  -0.0454  0.7085  1.0000
   1.500   0.3860   0.00594   0.00120  -0.0446  0.6321  1.0000
   2.000   0.4403   0.00638   0.00133  -0.0440  0.5587  1.0000
   2.500   0.4948   0.00684   0.00151  -0.0436  0.4883  1.0000
   3.000   0.5494   0.00734   0.00177  -0.0432  0.4198  1.0000
   3.500   0.6038   0.00789   0.00208  -0.0429  0.3538  1.0000
   4.000   0.6580   0.00850   0.00250  -0.0426  0.2888  1.0000
   4.500   0.7119   0.00919   0.00298  -0.0423  0.2246  1.0000
   5.000   0.7653   0.00999   0.00360  -0.0419  0.1644  1.0000
   5.500   0.8182   0.01091   0.00433  -0.0415  0.1111  1.0000
   6.000   0.8705   0.01195   0.00524  -0.0410  0.0687  1.0000
   6.500   0.9218   0.01327   0.00650  -0.0404  0.0377  1.0000
   7.500   1.0179   0.01748   0.01103  -0.0380  0.0122  1.0000
   8.000   1.0626   0.02032   0.01428  -0.0363  0.0102  1.0000
   8.500   1.1035   0.02408   0.01849  -0.0342  0.0092  1.0000
   9.000   1.1421   0.02750   0.02226  -0.0326  0.0079  1.0000
  10.000   1.1564   0.04438   0.04084  -0.0272  0.0071  1.0000
  10.500   1.1324   0.05267   0.04968  -0.0258  0.0071  1.0000