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 =     0.300 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
   0.000   0.2325   0.00586   0.00173  -0.0505  0.9613  1.0000
   0.500   0.3010   0.00586   0.00158  -0.0522  0.9017  1.0000
   1.000   0.3519   0.00610   0.00149  -0.0499  0.8185  1.0000
   1.500   0.4025   0.00652   0.00152  -0.0479  0.7311  1.0000
   2.000   0.4545   0.00702   0.00165  -0.0466  0.6457  1.0000
   2.500   0.5074   0.00757   0.00184  -0.0456  0.5630  1.0000
   3.000   0.5605   0.00816   0.00214  -0.0449  0.4812  1.0000
   3.500   0.6138   0.00881   0.00249  -0.0443  0.4009  1.0000
   4.000   0.6670   0.00954   0.00298  -0.0438  0.3227  1.0000
   4.500   0.7200   0.01034   0.00355  -0.0434  0.2492  1.0000
   5.000   0.7726   0.01127   0.00427  -0.0429  0.1830  1.0000
   5.500   0.8247   0.01234   0.00519  -0.0424  0.1261  1.0000
   6.000   0.8760   0.01360   0.00633  -0.0418  0.0824  1.0000
   6.500   0.9264   0.01510   0.00788  -0.0410  0.0501  1.0000
   8.000   1.0600   0.02436   0.01787  -0.0360  0.0144  1.0000
   8.500   1.0932   0.03108   0.02545  -0.0333  0.0135  1.0000
   9.000   1.1156   0.03884   0.03419  -0.0307  0.0132  1.0000
   9.500   1.1284   0.04584   0.04199  -0.0286  0.0120  1.0000
  10.000   1.1113   0.05505   0.05188  -0.0274  0.0117  1.0000
  10.500   1.0707   0.06725   0.06451  -0.0346  0.0121  1.0000