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 =     0.025 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -1.000  -0.0869   0.04238   0.03110  -0.0371   1.0000   0.2256
   0.000   0.0182   0.03912   0.02622  -0.0392   1.0000   0.2434
   1.000   0.1026   0.03528   0.02491  -0.0378   1.0000   0.9514
   2.000   0.1734   0.03987   0.02646  -0.0356   1.0000   1.0000
   3.000   0.2308   0.04547   0.03109  -0.0366   1.0000   1.0000
   4.000   0.3258   0.05387   0.03896  -0.0463   0.9666   1.0000
   5.000   0.4313   0.06523   0.05027  -0.0583   0.9161   1.0000
   6.000   0.3816   0.06846   0.05344  -0.0436   1.0000   1.0000
   7.000   0.4268   0.07789   0.06285  -0.0468   1.0000   1.0000
   8.000   0.5000   0.09038   0.07551  -0.0570   0.9644   1.0000
   9.000   0.5953   0.10729   0.09277  -0.0706   0.8871   1.0000
  10.000   0.6699   0.12510   0.11099  -0.0788   0.8136   1.0000