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 =     0.040 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
   0.000   0.0975   0.03713   0.02589  -0.0522   0.9456   0.1577
   1.000   0.2707   0.03431   0.02412  -0.0621   0.8911   1.0000
   2.000   0.4042   0.03888   0.02749  -0.0695   0.8308   1.0000
   3.000   0.5061   0.04371   0.03212  -0.0719   0.7725   1.0000
   4.000   0.6245   0.04847   0.03662  -0.0745   0.7123   1.0000
   5.000   0.7252   0.05369   0.04183  -0.0740   0.6559   1.0000
   6.000   0.7434   0.06276   0.05096  -0.0697   0.6082   1.0000
   7.000   0.7591   0.07318   0.06151  -0.0670   0.5631   1.0000
   8.000   0.7820   0.08571   0.07426  -0.0667   0.5317   1.0000
   9.000   0.7700   0.10098   0.08978  -0.0688   0.5251   1.0000
  10.000   0.8422   0.11675   0.10633  -0.0706   0.4895   1.0000