Airfoil: S822
Builder: M. Allen
Comment: plain trip @ x/c = 2% u.s. & 5% l.s. (h/c = 0.19%; w/c = 1.0%)

Number of Reynolds #'s:
 1 

Average Reynolds #:
 100900 
Number of angles of attack:
 49 
 alpha /   Cl   /  Cm
 -6.66  -0.631  -0.0700
 -4.99  -0.458  -0.0700
 -3.84  -0.313  -0.0700
 -2.90  -0.239  -0.0700
 -1.92  -0.149  -0.0700
 -0.77  -0.084  -0.0700
  0.23  -0.030  -0.0700
  1.25   0.019  -0.0700
  2.12   0.104  -0.0700
  3.16   0.176  -0.0700
  4.31   0.648  -0.0700
  5.36   0.741  -0.0700
  6.36   0.734  -0.0700
  7.37   0.770  -0.0700
  8.38   0.828  -0.0700
  9.38   0.892  -0.0700
 10.47   0.964  -0.0700
 11.39   1.023  -0.0700
 12.45   1.083  -0.0700
 13.44   1.121  -0.0700
 14.41   1.146  -0.0700
 15.50   1.150  -0.0700
 16.44   0.896  -0.0700
 17.30   0.762  -0.0700
 18.41   0.794  -0.0700
 16.85   0.854  -0.0700
 15.86   0.901  -0.0700
 15.01   0.905  -0.0700
 13.89   1.145  -0.0700
 13.01   1.120  -0.0700
 11.94   1.059  -0.0700
 10.85   0.991  -0.0700
 10.02   0.936  -0.0700
  8.90   0.863  -0.0700
  7.76   0.793  -0.0700
  6.89   0.750  -0.0700
  5.96   0.728  -0.0700
  4.73   0.692  -0.0700
  3.80   0.543  -0.0700
  2.76   0.155  -0.0700
  1.85   0.075  -0.0700
  0.63  -0.021  -0.0700
 -0.31  -0.058  -0.0700
 -1.34  -0.107  -0.0700
 -2.29  -0.176  -0.0700
 -3.27  -0.271  -0.0700
 -4.28  -0.349  -0.0700
 -5.48  -0.502  -0.0700
 -6.43  -0.594  -0.0700
Tabulated from data in file CL00731.DAT & reduced using program Q02.00L

File s822t2.lft created on 09-12-1997 at 13:46:18 using program FORMAT