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 =     0.055 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -1.000   0.0898   0.03503   0.02564  -0.0633   0.9024   0.1116
   0.000   0.2542   0.03101   0.02064  -0.0702   0.8578   0.1472
   1.000   0.4250   0.02880   0.01941  -0.0784   0.8121   1.0000
   2.000   0.5596   0.03047   0.02068  -0.0807   0.7597   1.0000
   3.000   0.6671   0.03178   0.02163  -0.0781   0.7067   1.0000
   4.000   0.7615   0.03385   0.02357  -0.0743   0.6546   1.0000
   5.000   0.8551   0.03597   0.02571  -0.0699   0.6012   1.0000
   6.000   0.9433   0.03855   0.02846  -0.0653   0.5482   1.0000
   7.000   1.0063   0.04370   0.03430  -0.0604   0.4987   1.0000
   8.000   1.0448   0.05104   0.04207  -0.0547   0.4490   1.0000
   9.000   0.9367   0.07658   0.06762  -0.0550   0.4082   1.0000
  10.000   0.9273   0.09176   0.08304  -0.0551   0.3675   1.0000