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 =     0.450 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
   0.000   0.1708   0.00542   0.00119  -0.0288  0.7269  1.0000
   0.500   0.2252   0.00571   0.00120  -0.0282  0.6873  1.0000
   1.000   0.2802   0.00590   0.00119  -0.0277  0.6437  1.0000
   1.500   0.3350   0.00614   0.00120  -0.0272  0.5951  1.0000
   2.000   0.3898   0.00643   0.00129  -0.0267  0.5428  1.0000
   2.500   0.4446   0.00677   0.00142  -0.0263  0.4869  1.0000
   3.000   0.4992   0.00719   0.00161  -0.0260  0.4226  1.0000
   3.500   0.5535   0.00772   0.00190  -0.0257  0.3523  1.0000
   4.000   0.6075   0.00835   0.00226  -0.0254  0.2807  1.0000
   4.500   0.6612   0.00907   0.00276  -0.0251  0.2132  1.0000
   5.000   0.7147   0.00985   0.00334  -0.0248  0.1583  1.0000
   5.500   0.7681   0.01065   0.00404  -0.0245  0.1181  1.0000
   6.000   0.8209   0.01154   0.00484  -0.0241  0.0869  1.0000
   6.500   0.8733   0.01253   0.00583  -0.0237  0.0611  1.0000
   7.000   0.9253   0.01357   0.00694  -0.0231  0.0426  1.0000
   7.500   0.9754   0.01504   0.00847  -0.0224  0.0285  1.0000
   9.000   1.1110   0.02241   0.01679  -0.0185  0.0137  1.0000
   9.500   1.1503   0.02554   0.02023  -0.0171  0.0114  1.0000
  10.500   1.1863   0.03860   0.03476  -0.0128  0.0097  1.0000
  11.000   1.1761   0.04621   0.04303  -0.0113  0.0093  1.0000
  11.500   1.1434   0.05745   0.05474  -0.0183  0.0094  1.0000
  12.000   1.1046   0.07525   0.07286  -0.0335  0.0096  1.0000
  12.500   1.0434   0.09970   0.09753  -0.0496  0.0102  1.0000