XFOIL         Version 6.94
  
 Calculated polar for: AG46ct  -02f rot.                               
  
 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   0.1789   0.00596   0.00151  -0.0311  0.8163  1.0000
   0.500   0.2298   0.00642   0.00147  -0.0294  0.7427  1.0000
   1.000   0.2829   0.00684   0.00156  -0.0284  0.6963  1.0000
   1.500   0.3371   0.00709   0.00163  -0.0277  0.6494  1.0000
   2.000   0.3913   0.00735   0.00171  -0.0270  0.5981  1.0000
   2.500   0.4453   0.00770   0.00183  -0.0263  0.5426  1.0000
   3.000   0.4993   0.00810   0.00203  -0.0257  0.4815  1.0000
   3.500   0.5531   0.00861   0.00232  -0.0252  0.4106  1.0000
   4.000   0.6064   0.00926   0.00271  -0.0247  0.3333  1.0000
   4.500   0.6594   0.01007   0.00326  -0.0244  0.2541  1.0000
   5.000   0.7121   0.01100   0.00395  -0.0240  0.1867  1.0000
   5.500   0.7644   0.01205   0.00484  -0.0236  0.1391  1.0000
   6.000   0.8167   0.01306   0.00583  -0.0231  0.1036  1.0000
   6.500   0.8678   0.01433   0.00706  -0.0225  0.0744  1.0000
   7.000   0.9186   0.01565   0.00849  -0.0219  0.0520  1.0000
   8.000   1.0118   0.02028   0.01347  -0.0195  0.0272  1.0000
   9.000   1.0955   0.02695   0.02096  -0.0164  0.0183  1.0000
  10.000   1.1325   0.04193   0.03772  -0.0122  0.0158  1.0000
  10.500   1.1284   0.04959   0.04606  -0.0114  0.0147  1.0000
  11.000   1.0925   0.06029   0.05725  -0.0165  0.0149  1.0000
  11.500   1.0357   0.08157   0.07888  -0.0347  0.0164  1.0000