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 =     0.020 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -2.000  -0.1989   0.04947   0.03916  -0.0298   1.0000   0.2881
  -1.000  -0.0773   0.04364   0.03095  -0.0378   1.0000   0.2711
   0.000   0.0296   0.04004   0.02601  -0.0399   1.0000   0.3119
   1.000   0.1115   0.03716   0.02431  -0.0362   1.0000   1.0000
   2.000   0.1770   0.04160   0.02636  -0.0350   1.0000   1.0000
   3.000   0.2344   0.04705   0.03082  -0.0358   1.0000   1.0000
   4.000   0.2878   0.05357   0.03682  -0.0374   1.0000   1.0000
   5.000   0.3376   0.06110   0.04435  -0.0397   1.0000   1.0000
   6.000   0.3847   0.06957   0.05265  -0.0425   1.0000   1.0000
   7.000   0.4295   0.07890   0.06196  -0.0457   1.0000   1.0000
   8.000   0.4725   0.08911   0.07228  -0.0493   1.0000   1.0000
   9.000   0.5138   0.10021   0.08360  -0.0533   1.0000   1.0000
  10.000   0.5840   0.11455   0.09842  -0.0648   0.9551   1.0000