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 =     0.300 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
   0.000   0.3138   0.00637   0.00203  -0.0690  0.8663  1.0000
   0.500   0.3669   0.00648   0.00191  -0.0677  0.8276  1.0000
   1.000   0.4205   0.00667   0.00187  -0.0666  0.7847  1.0000
   1.500   0.4744   0.00691   0.00188  -0.0657  0.7375  1.0000
   2.000   0.5283   0.00722   0.00198  -0.0648  0.6862  1.0000
   2.500   0.5821   0.00760   0.00212  -0.0641  0.6297  1.0000
   3.000   0.6356   0.00806   0.00237  -0.0634  0.5694  1.0000
   3.500   0.6889   0.00860   0.00267  -0.0627  0.5064  1.0000
   4.000   0.7419   0.00922   0.00310  -0.0622  0.4424  1.0000
   4.500   0.7945   0.00991   0.00359  -0.0616  0.3785  1.0000
   5.000   0.8467   0.01070   0.00421  -0.0611  0.3154  1.0000
   5.500   0.8984   0.01157   0.00491  -0.0605  0.2524  1.0000
   6.000   0.9490   0.01261   0.00576  -0.0599  0.1915  1.0000
   6.500   0.9988   0.01380   0.00680  -0.0592  0.1314  1.0000
   7.000   1.0465   0.01532   0.00811  -0.0583  0.0764  1.0000
   7.500   1.0905   0.01754   0.01017  -0.0568  0.0353  1.0000
   8.000   1.1321   0.02008   0.01292  -0.0547  0.0205  1.0000
   8.500   1.1209   0.01204   0.00554  -0.0457  0.0155  1.0000
   9.000   1.1513   0.01572   0.00954  -0.0424  0.0134  1.0000
   9.500   1.1751   0.02059   0.01479  -0.0387  0.0123  1.0000
  10.000   1.1866   0.02708   0.02181  -0.0341  0.0118  1.0000
  10.500   1.1719   0.03432   0.02958  -0.0279  0.0114  1.0000
  11.000   1.1351   0.04227   0.03804  -0.0227  0.0112  1.0000
  11.500   1.0973   0.05146   0.04763  -0.0217  0.0112  1.0000
  12.000   1.0600   0.06248   0.05901  -0.0238  0.0113  1.0000
  12.500   1.0203   0.07556   0.07240  -0.0285  0.0115  1.0000