XFOIL         Version 6.94
  
 Calculated polar for: AG47c -03f                                      
  
 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   0.0146   0.00545   0.00161  -0.0184  1.0000  1.0000
   0.500   0.0709   0.00547   0.00150  -0.0185  0.9964  1.0000
   1.000   0.1486   0.00568   0.00135  -0.0223  0.8537  1.0000
   1.500   0.1979   0.00615   0.00133  -0.0201  0.7705  1.0000
   2.000   0.2505   0.00659   0.00144  -0.0189  0.7225  1.0000
   2.500   0.3043   0.00693   0.00160  -0.0181  0.6805  1.0000
   3.000   0.3588   0.00708   0.00167  -0.0174  0.6280  1.0000
   3.500   0.4126   0.00738   0.00174  -0.0166  0.5506  1.0000
   4.000   0.4656   0.00800   0.00193  -0.0160  0.4366  1.0000
   4.500   0.5184   0.00895   0.00236  -0.0156  0.2955  1.0000
   5.000   0.5710   0.01018   0.00303  -0.0155  0.1699  1.0000
   5.500   0.6243   0.01129   0.00393  -0.0153  0.1107  1.0000
   6.000   0.6774   0.01242   0.00500  -0.0149  0.0805  1.0000
   7.500   0.8320   0.01745   0.01045  -0.0130  0.0356  1.0000
   8.000   0.8797   0.02084   0.01418  -0.0121  0.0283  1.0000
   8.500   0.9277   0.02442   0.01837  -0.0109  0.0252  1.0000
   9.000   0.9719   0.02839   0.02293  -0.0101  0.0219  1.0000
  10.000   1.0044   0.04855   0.04498  -0.0103  0.0195  1.0000
  10.500   0.9613   0.06807   0.06550  -0.0216  0.0217  1.0000