XFOIL         Version 6.94
  
 Calculated polar for: AG27 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   0.3259   0.00614   0.00190  -0.0698  0.8971  1.0000
   0.500   0.3772   0.00626   0.00178  -0.0678  0.8518  1.0000
   1.000   0.4288   0.00647   0.00172  -0.0660  0.8020  1.0000
   1.500   0.4813   0.00674   0.00173  -0.0646  0.7472  1.0000
   2.000   0.5342   0.00708   0.00181  -0.0634  0.6883  1.0000
   2.500   0.5873   0.00750   0.00196  -0.0624  0.6253  1.0000
   3.000   0.6403   0.00799   0.00221  -0.0615  0.5562  1.0000
   3.500   0.6929   0.00859   0.00251  -0.0607  0.4796  1.0000
   4.000   0.7452   0.00932   0.00296  -0.0600  0.3957  1.0000
   4.500   0.7969   0.01021   0.00351  -0.0594  0.3082  1.0000
   5.000   0.8482   0.01123   0.00425  -0.0588  0.2280  1.0000
   5.500   0.8989   0.01237   0.00513  -0.0581  0.1675  1.0000
   6.000   0.9495   0.01352   0.00616  -0.0574  0.1259  1.0000
   6.500   1.0000   0.01466   0.00734  -0.0566  0.0952  1.0000
   7.000   1.0493   0.01596   0.00867  -0.0557  0.0702  1.0000
   7.500   1.0970   0.01752   0.01029  -0.0545  0.0480  1.0000
   8.500   1.1807   0.02280   0.01595  -0.0507  0.0192  1.0000
   9.000   1.2200   0.02590   0.01943  -0.0483  0.0153  1.0000
   9.500   1.2442   0.03183   0.02589  -0.0450  0.0125  1.0000
  10.000   1.2713   0.03609   0.03083  -0.0420  0.0111  1.0000
  10.500   1.2769   0.04280   0.03826  -0.0380  0.0105  1.0000
  11.000   1.2566   0.05003   0.04612  -0.0334  0.0102  1.0000
  11.500   1.2218   0.05961   0.05621  -0.0343  0.0103  1.0000
  12.000   1.1830   0.07377   0.07081  -0.0434  0.0105  1.0000
  12.500   1.1403   0.09297   0.09033  -0.0575  0.0109  1.0000
  13.000   1.0890   0.11646   0.11397  -0.0720  0.0117  1.0000