XFOIL         Version 6.94
  
 Calculated polar for: AG25 Bubble Dancer DLG by Mark Drela            
  
 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   0.3073   0.00529   0.00143  -0.0665  0.8164  1.0000
   0.500   0.3622   0.00548   0.00136  -0.0659  0.7747  1.0000
   1.000   0.4173   0.00571   0.00136  -0.0653  0.7294  1.0000
   1.500   0.4722   0.00599   0.00140  -0.0649  0.6797  1.0000
   2.000   0.5271   0.00633   0.00151  -0.0644  0.6256  1.0000
   2.500   0.5817   0.00673   0.00167  -0.0640  0.5682  1.0000
   3.000   0.6360   0.00720   0.00192  -0.0636  0.5086  1.0000
   3.500   0.6903   0.00771   0.00221  -0.0633  0.4480  1.0000
   4.000   0.7441   0.00829   0.00260  -0.0630  0.3877  1.0000
   4.500   0.7976   0.00894   0.00304  -0.0626  0.3285  1.0000
   5.000   0.8507   0.00965   0.00359  -0.0623  0.2693  1.0000
   5.500   0.9032   0.01046   0.00421  -0.0619  0.2118  1.0000
   6.000   0.9548   0.01140   0.00495  -0.0614  0.1559  1.0000
   6.500   1.0053   0.01250   0.00588  -0.0608  0.1025  1.0000
   7.000   1.0543   0.01382   0.00700  -0.0600  0.0563  1.0000
   7.500   1.1009   0.01561   0.00869  -0.0588  0.0244  1.0000
   8.500   1.1824   0.02083   0.01441  -0.0544  0.0103  1.0000
   9.000   1.2193   0.02384   0.01775  -0.0517  0.0091  1.0000
   9.500   1.2547   0.02668   0.02086  -0.0493  0.0079  1.0000
  10.000   1.2762   0.03143   0.02603  -0.0458  0.0069  1.0000
  10.500   1.2745   0.03933   0.03464  -0.0405  0.0066  1.0000
  11.000   1.2705   0.04398   0.03977  -0.0355  0.0065  1.0000
  11.500   1.2500   0.05081   0.04707  -0.0329  0.0064  1.0000
  12.000   1.2200   0.06089   0.05759  -0.0356  0.0064  1.0000
  12.500   1.1858   0.07431   0.07140  -0.0433  0.0064  1.0000