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 =     0.450 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
   0.000   0.0183   0.00451   0.00136  -0.0191  0.9757  0.9658
   0.500   0.0848   0.00486   0.00112  -0.0203  0.8054  1.0000
   1.000   0.1372   0.00526   0.00106  -0.0191  0.7456  1.0000
   1.500   0.1915   0.00558   0.00110  -0.0185  0.7100  1.0000
   2.000   0.2467   0.00577   0.00117  -0.0180  0.6752  1.0000
   2.500   0.3019   0.00588   0.00116  -0.0175  0.6297  1.0000
   3.000   0.3566   0.00615   0.00120  -0.0170  0.5618  1.0000
   3.500   0.4108   0.00662   0.00132  -0.0165  0.4677  1.0000
   4.000   0.4648   0.00732   0.00158  -0.0163  0.3510  1.0000
   4.500   0.5184   0.00825   0.00202  -0.0162  0.2244  1.0000
   5.000   0.5722   0.00916   0.00257  -0.0161  0.1376  1.0000
   5.500   0.6263   0.01001   0.00327  -0.0159  0.0937  1.0000
   6.000   0.6802   0.01084   0.00404  -0.0157  0.0677  1.0000
   6.500   0.7337   0.01182   0.00509  -0.0153  0.0500  1.0000
   7.000   0.7865   0.01300   0.00637  -0.0149  0.0372  1.0000
   7.500   0.8379   0.01461   0.00812  -0.0143  0.0277  1.0000
   8.000   0.8895   0.01610   0.00986  -0.0137  0.0226  1.0000
   9.000   0.9827   0.02274   0.01740  -0.0116  0.0165  1.0000
   9.500   1.0250   0.02698   0.02226  -0.0106  0.0147  1.0000
  10.000   1.0616   0.03139   0.02715  -0.0101  0.0128  1.0000
  12.000   0.8868   0.12123   0.11903  -0.0599  0.0182  1.0000