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 =     0.300 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
   0.000   0.1096   0.00555   0.00143  -0.0186  1.0000  1.0000
   0.500   0.1967   0.00561   0.00138  -0.0251  0.9222  1.0000
   1.000   0.2502   0.00603   0.00131  -0.0232  0.7849  1.0000
   1.500   0.3011   0.00656   0.00142  -0.0215  0.7133  1.0000
   2.000   0.3544   0.00691   0.00158  -0.0205  0.6482  1.0000
   2.500   0.4071   0.00732   0.00168  -0.0195  0.5550  1.0000
   3.000   0.4593   0.00804   0.00190  -0.0186  0.4266  1.0000
   3.500   0.5116   0.00899   0.00234  -0.0181  0.2902  1.0000
   4.000   0.5642   0.01006   0.00294  -0.0178  0.1830  1.0000
   4.500   0.6172   0.01109   0.00375  -0.0175  0.1213  1.0000
   5.000   0.6700   0.01221   0.00478  -0.0170  0.0871  1.0000
   6.500   0.8238   0.01708   0.00999  -0.0146  0.0375  1.0000
   7.000   0.8717   0.02003   0.01323  -0.0136  0.0290  1.0000
   7.500   0.9199   0.02336   0.01715  -0.0123  0.0259  1.0000
   8.000   0.9636   0.02781   0.02227  -0.0110  0.0228  1.0000
   8.500   0.9986   0.03344   0.02850  -0.0101  0.0200  1.0000
   9.000   1.0042   0.04585   0.04208  -0.0100  0.0195  1.0000
   9.500   0.9955   0.05715   0.05413  -0.0125  0.0197  1.0000