XFOIL         Version 6.94
  
 Calculated polar for: AG47ct  -02f rot.                               
  
 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   0.1418   0.00456   0.00110  -0.0250  0.9097  1.0000
   0.500   0.1905   0.00508   0.00099  -0.0224  0.7654  1.0000
   1.000   0.2432   0.00551   0.00104  -0.0213  0.7071  1.0000
   1.500   0.2977   0.00576   0.00111  -0.0207  0.6514  1.0000
   2.000   0.3517   0.00609   0.00116  -0.0200  0.5715  1.0000
   2.500   0.4051   0.00665   0.00131  -0.0194  0.4620  1.0000
   3.000   0.4585   0.00739   0.00157  -0.0190  0.3392  1.0000
   3.500   0.5119   0.00824   0.00199  -0.0187  0.2263  1.0000
   4.000   0.5657   0.00903   0.00248  -0.0185  0.1509  1.0000
   4.500   0.6194   0.00986   0.00312  -0.0182  0.1023  1.0000
   5.000   0.6731   0.01065   0.00386  -0.0178  0.0732  1.0000
   5.500   0.7261   0.01169   0.00490  -0.0173  0.0526  1.0000
   6.000   0.7787   0.01282   0.00613  -0.0167  0.0390  1.0000
   6.500   0.8295   0.01451   0.00797  -0.0159  0.0286  1.0000
   7.000   0.8814   0.01576   0.00947  -0.0152  0.0236  1.0000
   7.500   0.9249   0.02026   0.01442  -0.0137  0.0192  1.0000
   8.000   0.9749   0.02188   0.01640  -0.0128  0.0170  1.0000
   8.500   1.0178   0.02588   0.02101  -0.0115  0.0151  1.0000
   9.000   1.0571   0.02967   0.02527  -0.0107  0.0133  1.0000
  10.000   1.0431   0.05332   0.05087  -0.0136  0.0116  1.0000
  10.500   1.0058   0.07205   0.06995  -0.0327  0.0121  1.0000
  11.000   0.8901   0.11788   0.11569  -0.0578  0.0179  1.0000