Airfoil: S822
Builder: M. Allen
Comment: clean

Number of Reynolds #'s:
 1 

Average Reynolds #:
 101200 
Number of angles of attack:
 49 
 alpha /   Cl   /  Cm
 -6.30  -0.547  -0.0700
 -4.94  -0.383  -0.0700
 -3.95  -0.320  -0.0700
 -2.94  -0.245  -0.0700
 -2.02  -0.223  -0.0700
 -0.83  -0.174  -0.0700
  0.15  -0.083  -0.0700
  1.14  -0.002  -0.0700
  2.14   0.081  -0.0700
  3.15   0.172  -0.0700
  4.16   0.274  -0.0700
  5.19   0.396  -0.0700
  6.28   0.709  -0.0700
  7.34   0.902  -0.0700
  8.43   0.985  -0.0700
  9.32   1.042  -0.0700
 10.45   1.061  -0.0700
 11.39   1.080  -0.0700
 12.45   1.109  -0.0700
 13.37   1.124  -0.0700
 14.39   1.130  -0.0700
 15.44   1.117  -0.0700
 16.26   0.795  -0.0700
 17.31   0.793  -0.0700
 18.30   0.807  -0.0700
 17.01   0.794  -0.0700
 15.98   0.811  -0.0700
 14.96   0.904  -0.0700
 14.03   1.125  -0.0700
 12.99   1.115  -0.0700
 12.05   1.098  -0.0700
 11.09   1.071  -0.0700
 10.09   1.060  -0.0700
  9.05   1.025  -0.0700
  7.93   0.953  -0.0700
  7.05   0.863  -0.0700
  5.90   0.540  -0.0700
  4.79   0.319  -0.0700
  3.89   0.235  -0.0700
  2.73   0.123  -0.0700
  1.87   0.043  -0.0700
  0.73  -0.052  -0.0700
 -0.26  -0.135  -0.0700
 -1.25  -0.209  -0.0700
 -2.22  -0.237  -0.0700
 -3.31  -0.282  -0.0700
 -4.29  -0.349  -0.0700
 -5.26  -0.410  -0.0700
 -6.35  -0.545  -0.0700
Tabulated from data in file CL00728.DAT & reduced using program Q02.00L

File s822.lft created on 09-12-1997 at 13:46:18 using program FORMAT