XFOIL         Version 6.94
  
 Calculated polar for: AG13                                            
  
 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   0.2427   0.00474   0.00121  -0.0513  0.8958  1.0000
   0.500   0.2932   0.00501   0.00111  -0.0492  0.8127  1.0000
   1.000   0.3452   0.00542   0.00110  -0.0478  0.7280  1.0000
   1.500   0.3984   0.00586   0.00116  -0.0468  0.6464  1.0000
   2.000   0.4523   0.00633   0.00130  -0.0461  0.5678  1.0000
   2.500   0.5065   0.00682   0.00148  -0.0456  0.4904  1.0000
   3.000   0.5607   0.00736   0.00175  -0.0452  0.4163  1.0000
   3.500   0.6149   0.00795   0.00207  -0.0449  0.3418  1.0000
   4.000   0.6688   0.00860   0.00250  -0.0446  0.2725  1.0000
   4.500   0.7225   0.00932   0.00301  -0.0442  0.2105  1.0000
   5.000   0.7758   0.01011   0.00361  -0.0439  0.1531  1.0000
   5.500   0.8285   0.01103   0.00439  -0.0434  0.1043  1.0000
   6.000   0.8807   0.01209   0.00533  -0.0429  0.0669  1.0000
   6.500   0.9325   0.01319   0.00645  -0.0423  0.0392  1.0000
   7.500   1.0287   0.01739   0.01098  -0.0398  0.0129  1.0000
   8.000   1.0743   0.01995   0.01386  -0.0382  0.0102  1.0000
   8.500   1.1122   0.02435   0.01875  -0.0360  0.0088  1.0000
   9.000   1.1456   0.02949   0.02458  -0.0338  0.0078  1.0000
   9.500   1.1694   0.03574   0.03158  -0.0312  0.0073  1.0000
  10.000   1.1708   0.04416   0.04083  -0.0287  0.0070  1.0000
  10.500   1.1422   0.05334   0.05059  -0.0276  0.0070  1.0000
  11.000   1.1058   0.06776   0.06542  -0.0396  0.0072  1.0000
  11.500   1.0662   0.08949   0.08741  -0.0570  0.0076  1.0000