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 =     0.010 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
   0.000   0.0480   0.04228   0.02550  -0.0361   1.0000   1.0000
   1.000   0.1217   0.04540   0.02473  -0.0333   1.0000   1.0000
   2.000   0.1832   0.04929   0.02665  -0.0322   1.0000   1.0000
   3.000   0.2408   0.05413   0.03026  -0.0321   1.0000   1.0000
   4.000   0.2949   0.05997   0.03536  -0.0330   1.0000   1.0000
   5.000   0.3456   0.06683   0.04183  -0.0345   1.0000   1.0000
   6.000   0.3932   0.07471   0.04959  -0.0368   1.0000   1.0000
   7.000   0.4381   0.08360   0.05860  -0.0396   1.0000   1.0000
   8.000   0.4806   0.09343   0.06870  -0.0429   1.0000   1.0000
   9.000   0.5209   0.10413   0.07986  -0.0468   1.0000   1.0000
  10.000   0.5595   0.11559   0.09188  -0.0511   1.0000   1.0000