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 =     0.045 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -1.000  -0.0164   0.03863   0.02932  -0.0496   0.9580   0.1434
   0.000   0.1643   0.03533   0.02438  -0.0610   0.9087   0.1521
   1.000   0.3236   0.03297   0.02302  -0.0681   0.8563   1.0000
   2.000   0.4371   0.03658   0.02577  -0.0712   0.7965   1.0000
   3.000   0.5448   0.04072   0.02972  -0.0730   0.7395   1.0000
   4.000   0.6327   0.04531   0.03410  -0.0720   0.6824   1.0000
   5.000   0.7102   0.05052   0.03928  -0.0695   0.6252   1.0000
   6.000   0.7619   0.05836   0.04722  -0.0669   0.5767   1.0000
   7.000   0.8112   0.06707   0.05612  -0.0645   0.5310   1.0000
   8.000   0.8745   0.07539   0.06508  -0.0618   0.4862   1.0000
   9.000   0.8241   0.09339   0.08320  -0.0638   0.4639   1.0000
  10.000   0.8552   0.10605   0.09621  -0.0635   0.4249   1.0000