Airfoil: S1223
Builder: Y. Tinel
Comment: clean

Number of Reynolds #'s:
 2 

Average Reynolds #:
 149500 
Number of angles of attack:
 55 
 alpha /   Cl   /  Cm
 -4.43   0.132  -0.2900
 -3.39   0.344  -0.2900
 -2.33   0.781  -0.2900
 -1.25   0.913  -0.2900
 -0.32   1.021  -0.2900
  0.79   1.132  -0.2900
  1.72   1.218  -0.2900
  2.88   1.319  -0.2900
  3.87   1.391  -0.2900
  4.85   1.473  -0.2900
  5.82   1.548  -0.2900
  7.01   1.636  -0.2900
  7.95   1.704  -0.2900
  8.85   1.761  -0.2900
  9.98   1.827  -0.2900
 11.10   1.892  -0.2900
 11.88   1.938  -0.2900
 13.07   1.994  -0.2900
 14.03   2.058  -0.2900
 15.08   2.124  -0.2900
 16.10   2.188  -0.2900
 17.14   2.205  -0.2900
 17.99   2.169  -0.2900
 18.95   2.057  -0.2900
 20.06   2.021  -0.2900
 20.95   1.929  -0.2900
 21.65   1.461  -0.2900
 23.02   1.477  -0.2900
 23.79   1.526  -0.2900
 22.41   1.457  -0.2900
 21.32   1.421  -0.2900
 20.26   1.407  -0.2900
 19.35   1.357  -0.2900
 18.49   1.373  -0.2900
 17.28   1.321  -0.2900
 16.46   1.294  -0.2900
 15.31   1.228  -0.2900
 14.30   1.294  -0.2900
 13.32   1.224  -0.2900
 12.23   1.156  -0.2900
 11.19   1.114  -0.2900
 10.30   1.152  -0.2900
  9.33   1.135  -0.2900
  8.27   1.093  -0.2900
  7.21   1.104  -0.2900
  6.36   1.479  -0.2900
  5.38   1.497  -0.2900
  4.43   1.421  -0.2900
  3.40   1.341  -0.2900
  2.36   1.250  -0.2900
  1.30   1.156  -0.2900
  0.27   1.059  -0.2900
 -0.79   0.940  -0.2900
 -1.82   0.828  -0.2900
 -2.91   0.464  -0.2900
Tabulated from data in file CL00697.DAT & reduced using program Q02.00L

Average Reynolds #:
 198900 
Number of angles of attack:
 59 
 alpha /   Cl   /  Cm
 -5.53   0.077  -0.2900
 -4.35   0.235  -0.2900
 -3.45   0.341  -0.2900
 -2.29   0.786  -0.2900
 -1.20   0.911  -0.2900
 -0.32   1.014  -0.2900
  0.87   1.138  -0.2900
  1.88   1.237  -0.2900
  2.91   1.331  -0.2900
  3.96   1.418  -0.2900
  4.81   1.488  -0.2900
  6.10   1.604  -0.2900
  6.89   1.666  -0.2900
  7.93   1.741  -0.2900
  8.98   1.809  -0.2900
 10.00   1.873  -0.2900
 11.14   1.945  -0.2900
 11.99   1.992  -0.2900
 13.17   2.061  -0.2900
 14.12   2.116  -0.2900
 15.05   2.170  -0.2900
 16.20   2.209  -0.2900
 17.11   2.203  -0.2900
 17.99   2.135  -0.2900
 18.95   2.037  -0.2900
 20.01   1.986  -0.2900
 21.07   1.946  -0.2900
 22.04   1.935  -0.2900
 23.14   1.897  -0.2900
 23.88   1.886  -0.2900
 22.52   1.915  -0.2900
 21.55   1.931  -0.2900
 20.50   1.995  -0.2900
 19.59   2.019  -0.2900
 18.65   2.067  -0.2900
 17.62   2.169  -0.2900
 16.57   2.214  -0.2900
 15.60   2.190  -0.2900
 14.59   2.149  -0.2900
 13.56   2.087  -0.2900
 12.49   2.025  -0.2900
 11.62   1.971  -0.2900
 10.50   1.897  -0.2900
  9.45   1.830  -0.2900
  8.39   1.756  -0.2900
  7.40   1.688  -0.2900
  6.39   1.614  -0.2900
  5.34   1.527  -0.2900
  4.34   1.429  -0.2900
  3.21   1.344  -0.2900
  2.18   1.247  -0.2900
  1.17   1.151  -0.2900
  0.16   1.054  -0.2900
 -0.84   0.939  -0.2900
 -1.85   0.827  -0.2900
 -2.74   0.542  -0.2900
 -3.81   0.295  -0.2900
 -4.94   0.167  -0.2900
 -5.85   0.032  -0.2900
Tabulated from data in file CL00698.DAT & reduced using program Q02.00L

File s1223.lft created on 09-12-1997 at 13:46:18 using program FORMAT