XFOIL         Version 6.96
  
 Calculated polar for: AQUILA 9.3% smoothed
                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.035 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -2.000  -0.2157   0.04808   0.04042  -0.0290   1.0000   0.2636
  -1.000  -0.0982   0.04113   0.03156  -0.0365   1.0000   0.1825
   0.000   0.0018   0.03801   0.02672  -0.0379   0.9985   0.1658
   1.000   0.1933   0.03481   0.02510  -0.0526   0.9429   1.0000
   2.000   0.3454   0.04104   0.02904  -0.0639   0.8810   1.0000
   3.000   0.4799   0.04773   0.03516  -0.0725   0.8184   1.0000
   4.000   0.5667   0.05357   0.04092  -0.0731   0.7545   1.0000
   5.000   0.6409   0.06080   0.04807  -0.0731   0.7020   1.0000
   6.000   0.7219   0.06955   0.05693  -0.0737   0.6519   1.0000
   7.000   0.7190   0.07885   0.06634  -0.0700   0.6116   1.0000
   8.000   0.7599   0.09376   0.08153  -0.0726   0.5957   1.0000
  10.000   0.7830   0.13511   0.12386  -0.0851   0.6525   1.0000