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 =     0.450 e 6     Ncrit =   9.000
  
  alpha     CL        CD       CDp       CM    Top_Xtr Bot_Xtr
 ------- -------- --------- --------- -------- ------- -------
   0.000   0.3168   0.00509   0.00135  -0.0664  0.8418  1.0000
   0.500   0.3700   0.00530   0.00127  -0.0652  0.7924  1.0000
   1.000   0.4237   0.00557   0.00125  -0.0642  0.7387  1.0000
   1.500   0.4777   0.00589   0.00129  -0.0634  0.6817  1.0000
   2.000   0.5318   0.00627   0.00139  -0.0627  0.6222  1.0000
   2.500   0.5860   0.00668   0.00155  -0.0621  0.5577  1.0000
   3.000   0.6398   0.00720   0.00179  -0.0616  0.4864  1.0000
   3.500   0.6933   0.00780   0.00210  -0.0611  0.4103  1.0000
   4.500   0.7992   0.00930   0.00303  -0.0602  0.2560  1.0000
   5.000   0.8514   0.01019   0.00366  -0.0598  0.1889  1.0000
   5.500   0.9035   0.01111   0.00439  -0.0593  0.1405  1.0000
   6.000   0.9556   0.01197   0.00518  -0.0587  0.1063  1.0000
   6.500   1.0071   0.01291   0.00612  -0.0581  0.0802  1.0000
   7.000   1.0579   0.01392   0.00713  -0.0573  0.0576  1.0000
   7.500   1.1072   0.01518   0.00842  -0.0565  0.0375  1.0000
   8.000   1.1544   0.01684   0.01011  -0.0553  0.0208  1.0000
   9.000   1.2392   0.02163   0.01543  -0.0515  0.0100  1.0000
  10.500   1.3164   0.03515   0.03050  -0.0418  0.0067  1.0000
  11.000   1.3146   0.04146   0.03744  -0.0373  0.0064  1.0000
  11.500   1.2884   0.04871   0.04521  -0.0335  0.0064  1.0000
  12.000   1.2555   0.05944   0.05641  -0.0371  0.0064  1.0000
  12.500   1.2190   0.07469   0.07206  -0.0474  0.0065  1.0000
  13.000   1.1785   0.09361   0.09128  -0.0603  0.0067  1.0000
  13.500   1.1332   0.11463   0.11250  -0.0725  0.0070  1.0000
  14.000   1.0788   0.13894   0.13691  -0.0849  0.0075  1.0000