Airfoil: S7075 (A)
Builder: J. Robertson
Comment: flap = 5 degs: Zig-Zag trip type "D" @ x/c = 68% (h/c = 0.25%)

Number of Reynolds #'s:
 4 

Average Reynolds #:
 59800 
Number of angles of attack:
 49 
 alpha /   Cl   /  Cm
 -6.24  -0.233  -0.1000
 -4.87  -0.057  -0.1000
 -3.73   0.048  -0.1000
 -2.70   0.131  -0.1000
 -1.77   0.195  -0.1000
 -0.76   0.288  -0.1000
  0.25   0.377  -0.1000
  1.29   0.476  -0.1000
  2.34   0.537  -0.1000
  3.43   0.764  -0.1000
  4.54   0.968  -0.1000
  5.50   1.000  -0.1000
  6.45   1.078  -0.1000
  7.50   1.132  -0.1000
  8.51   1.165  -0.1000
  9.60   1.199  -0.1000
 10.65   1.235  -0.1000
 11.47   1.254  -0.1000
 12.48   1.134  -0.1000
 13.51   1.014  -0.1000
 14.50   1.052  -0.1000
 15.44   1.042  -0.1000
 16.58   0.996  -0.1000
 17.43   0.992  -0.1000
 18.47   0.997  -0.1000
 17.14   1.019  -0.1000
 16.22   1.021  -0.1000
 15.07   1.050  -0.1000
 14.18   1.050  -0.1000
 13.03   1.062  -0.1000
 12.15   1.161  -0.1000
 11.24   1.255  -0.1000
 10.03   1.222  -0.1000
  9.08   1.192  -0.1000
  8.16   1.158  -0.1000
  7.19   1.126  -0.1000
  6.19   1.069  -0.1000
  5.19   1.003  -0.1000
  4.02   0.903  -0.1000
  3.08   0.685  -0.1000
  2.11   0.536  -0.1000
  0.97   0.453  -0.1000
  0.04   0.357  -0.1000
 -1.09   0.263  -0.1000
 -1.99   0.181  -0.1000
 -3.06   0.110  -0.1000
 -4.05   0.021  -0.1000
 -5.21  -0.112  -0.1000
 -6.12  -0.213  -0.1000
Tabulated from data in file CL00735.DAT & reduced using program Q02.00L

Average Reynolds #:
 100100 
Number of angles of attack:
 49 
 alpha /   Cl   /  Cm
 -6.17  -0.068  -0.1000
 -4.79   0.049  -0.1000
 -3.80   0.133  -0.1000
 -2.78   0.221  -0.1000
 -1.76   0.307  -0.1000
 -0.79   0.371  -0.1000
  0.43   0.476  -0.1000
  1.42   0.563  -0.1000
  2.31   0.674  -0.1000
  3.49   0.925  -0.1000
  4.53   1.024  -0.1000
  5.61   1.084  -0.1000
  6.53   1.151  -0.1000
  7.53   1.204  -0.1000
  8.51   1.225  -0.1000
  9.52   1.255  -0.1000
 10.59   1.289  -0.1000
 11.66   1.309  -0.1000
 12.46   1.246  -0.1000
 13.58   1.128  -0.1000
 14.58   1.112  -0.1000
 15.46   1.106  -0.1000
 16.58   1.064  -0.1000
 17.46   1.042  -0.1000
 18.52   1.077  -0.1000
 17.03   1.065  -0.1000
 16.11   1.081  -0.1000
 15.05   1.121  -0.1000
 14.03   1.099  -0.1000
 13.24   1.158  -0.1000
 12.14   1.312  -0.1000
 11.14   1.308  -0.1000
 10.19   1.279  -0.1000
  9.25   1.241  -0.1000
  8.15   1.212  -0.1000
  7.12   1.176  -0.1000
  6.01   1.097  -0.1000
  5.04   1.040  -0.1000
  4.15   0.980  -0.1000
  3.03   0.831  -0.1000
  2.10   0.618  -0.1000
  0.98   0.526  -0.1000
 -0.03   0.435  -0.1000
 -1.03   0.342  -0.1000
 -2.04   0.270  -0.1000
 -3.03   0.212  -0.1000
 -4.14   0.114  -0.1000
 -5.11   0.028  -0.1000
 -6.11  -0.051  -0.1000
Tabulated from data in file CL00737.DAT & reduced using program Q02.00L

Average Reynolds #:
 200200 
Number of angles of attack:
 49 
 alpha /   Cl   /  Cm
 -6.14  -0.029  -0.1000
 -4.79   0.098  -0.1000
 -3.68   0.207  -0.1000
 -2.70   0.298  -0.1000
 -1.61   0.394  -0.1000
 -0.51   0.499  -0.1000
  0.51   0.609  -0.1000
  1.30   0.709  -0.1000
  2.51   0.852  -0.1000
  3.39   0.936  -0.1000
  4.46   1.021  -0.1000
  5.57   1.094  -0.1000
  6.67   1.163  -0.1000
  7.56   1.203  -0.1000
  8.59   1.238  -0.1000
  9.51   1.270  -0.1000
 10.62   1.303  -0.1000
 11.61   1.320  -0.1000
 12.53   1.314  -0.1000
 13.44   1.224  -0.1000
 14.57   1.102  -0.1000
 15.42   1.106  -0.1000
 16.39   1.070  -0.1000
 17.47   1.034  -0.1000
 18.39   1.035  -0.1000
 16.83   1.049  -0.1000
 16.03   1.103  -0.1000
 14.85   1.098  -0.1000
 14.01   1.166  -0.1000
 13.16   1.261  -0.1000
 12.20   1.318  -0.1000
 11.08   1.311  -0.1000
 10.28   1.290  -0.1000
  9.06   1.250  -0.1000
  8.03   1.209  -0.1000
  7.07   1.176  -0.1000
  6.05   1.115  -0.1000
  5.00   1.047  -0.1000
  3.93   0.975  -0.1000
  3.07   0.896  -0.1000
  1.97   0.784  -0.1000
  1.01   0.657  -0.1000
 -0.05   0.539  -0.1000
 -1.16   0.428  -0.1000
 -2.21   0.331  -0.1000
 -3.25   0.238  -0.1000
 -4.19   0.152  -0.1000
 -5.32   0.047  -0.1000
 -6.23  -0.037  -0.1000
Tabulated from data in file CL00739.DAT & reduced using program Q02.00L

Average Reynolds #:
 300500 
Number of angles of attack:
 49 
 alpha /   Cl   /  Cm
 -6.12  -0.020  -0.1000
 -4.71   0.113  -0.1000
 -3.82   0.189  -0.1000
 -2.80   0.294  -0.1000
 -1.87   0.403  -0.1000
 -0.79   0.511  -0.1000
  0.27   0.620  -0.1000
  1.30   0.732  -0.1000
  2.45   0.856  -0.1000
  3.37   0.939  -0.1000
  4.45   1.019  -0.1000
  5.43   1.088  -0.1000
  6.45   1.152  -0.1000
  7.56   1.207  -0.1000
  8.47   1.248  -0.1000
  9.60   1.288  -0.1000
 10.64   1.320  -0.1000
 11.65   1.336  -0.1000
 12.68   1.333  -0.1000
 13.42   1.276  -0.1000
 14.37   1.190  -0.1000
 15.36   1.147  -0.1000
 16.37   1.087  -0.1000
 17.32   1.046  -0.1000
 18.40   1.038  -0.1000
 17.11   1.042  -0.1000
 16.17   1.098  -0.1000
 15.15   1.138  -0.1000
 14.26   1.213  -0.1000
 13.09   1.303  -0.1000
 12.08   1.332  -0.1000
 11.03   1.324  -0.1000
  9.99   1.297  -0.1000
  9.15   1.269  -0.1000
  7.97   1.221  -0.1000
  7.08   1.182  -0.1000
  6.03   1.123  -0.1000
  4.96   1.052  -0.1000
  3.95   0.978  -0.1000
  3.02   0.908  -0.1000
  1.88   0.793  -0.1000
  0.76   0.670  -0.1000
 -0.12   0.574  -0.1000
 -1.20   0.467  -0.1000
 -2.28   0.359  -0.1000
 -3.21   0.250  -0.1000
 -4.10   0.161  -0.1000
 -5.26   0.062  -0.1000
 -6.30  -0.034  -0.1000
Tabulated from data in file CL00741.DAT & reduced using program Q02.00L

File 7075atf5.lft created on 09-12-1997 at 13:46:18 using program FORMAT