Airfoil: E423 Builder: D. Glaze / M. Lazor Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 60200 Number of angles of attack: 49 alpha / Cl / Cm -6.29 -0.023 -0.2460 -5.20 -0.146 -0.2460 -4.26 -0.257 -0.2460 -3.16 -0.307 -0.2460 -2.25 -0.238 -0.2460 -1.07 -0.007 -0.2460 -0.13 0.166 -0.2460 0.81 0.342 -0.2460 1.95 0.463 -0.2460 2.93 0.533 -0.2460 3.90 0.604 -0.2460 5.04 0.667 -0.2460 5.99 0.714 -0.2460 6.97 0.761 -0.2460 8.13 0.798 -0.2460 8.96 0.833 -0.2460 10.00 0.886 -0.2460 11.03 0.911 -0.2460 12.22 0.971 -0.2460 13.02 0.986 -0.2460 14.03 1.054 -0.2460 14.98 1.097 -0.2460 16.22 1.133 -0.2460 17.15 1.177 -0.2460 18.06 1.235 -0.2460 16.34 1.142 -0.2460 15.51 1.126 -0.2460 14.46 1.087 -0.2460 13.41 1.043 -0.2460 12.32 0.982 -0.2460 11.46 0.938 -0.2460 10.39 0.910 -0.2460 9.55 0.875 -0.2460 8.36 0.828 -0.2460 7.40 0.806 -0.2460 6.54 0.762 -0.2460 5.34 0.710 -0.2460 4.48 0.666 -0.2460 3.35 0.592 -0.2460 2.32 0.518 -0.2460 1.27 0.414 -0.2460 0.42 0.294 -0.2460 -0.63 0.062 -0.2460 -1.91 -0.142 -0.2460 -2.87 -0.259 -0.2460 -3.88 -0.275 -0.2460 -4.85 -0.170 -0.2460 -5.84 -0.070 -0.2460 -6.76 0.033 -0.2460 Tabulated from data in file AG00843.DAT & reduced using program Q02.00L Average Reynolds #: 100300 Number of angles of attack: 49 alpha / Cl / Cm -6.74 0.161 -0.2460 -4.91 0.199 -0.2460 -4.18 0.233 -0.2460 -3.15 0.324 -0.2460 -2.15 0.489 -0.2460 -1.09 0.719 -0.2460 -0.06 0.823 -0.2460 1.13 0.921 -0.2460 2.12 0.999 -0.2460 3.12 1.091 -0.2460 4.12 1.173 -0.2460 5.14 0.825 -0.2460 6.04 0.874 -0.2460 7.07 0.888 -0.2460 7.95 0.933 -0.2460 8.99 0.975 -0.2460 10.14 1.037 -0.2460 11.12 1.105 -0.2460 12.06 1.109 -0.2460 13.03 1.175 -0.2460 13.99 1.162 -0.2460 15.11 1.156 -0.2460 16.22 1.216 -0.2460 17.20 1.246 -0.2460 18.14 1.226 -0.2460 16.36 1.225 -0.2460 15.65 1.199 -0.2460 14.33 1.159 -0.2460 13.62 1.154 -0.2460 12.45 1.100 -0.2460 11.36 1.081 -0.2460 10.50 1.050 -0.2460 9.38 0.984 -0.2460 8.48 0.970 -0.2460 7.29 0.934 -0.2460 6.49 0.937 -0.2460 5.41 0.882 -0.2460 4.50 0.783 -0.2460 3.53 1.108 -0.2460 2.51 1.031 -0.2460 1.32 0.919 -0.2460 0.43 0.856 -0.2460 -0.74 0.747 -0.2460 -1.66 0.611 -0.2460 -2.85 0.367 -0.2460 -3.64 0.272 -0.2460 -4.78 0.190 -0.2460 -5.75 0.174 -0.2460 -6.82 0.162 -0.2460 Tabulated from data in file AG00845.DAT & reduced using program Q02.00L Average Reynolds #: 199400 Number of angles of attack: 49 alpha / Cl / Cm -6.28 0.178 -0.2460 -5.07 0.215 -0.2460 -4.08 0.285 -0.2460 -3.02 0.411 -0.2460 -2.17 0.690 -0.2460 -0.87 0.838 -0.2460 -0.08 0.915 -0.2460 1.04 1.023 -0.2460 1.97 1.109 -0.2460 3.16 1.220 -0.2460 4.10 1.306 -0.2460 5.08 1.382 -0.2460 6.33 1.491 -0.2460 7.07 1.546 -0.2460 8.17 1.633 -0.2460 9.31 1.722 -0.2460 10.30 1.796 -0.2460 11.23 1.864 -0.2460 12.37 1.940 -0.2460 13.36 1.991 -0.2460 14.39 2.048 -0.2460 15.43 2.058 -0.2460 16.31 2.050 -0.2460 17.30 2.023 -0.2460 18.36 1.976 -0.2460 16.48 2.045 -0.2460 15.87 2.053 -0.2460 14.59 2.055 -0.2460 13.82 2.019 -0.2460 12.66 1.956 -0.2460 11.50 1.880 -0.2460 10.65 1.819 -0.2460 9.59 1.733 -0.2460 8.48 1.649 -0.2460 7.67 1.589 -0.2460 6.42 1.488 -0.2460 5.61 1.420 -0.2460 4.50 1.324 -0.2460 3.44 1.234 -0.2460 2.43 1.143 -0.2460 1.41 1.047 -0.2460 0.41 0.950 -0.2460 -0.60 0.850 -0.2460 -1.60 0.748 -0.2460 -2.55 0.498 -0.2460 -3.78 0.312 -0.2460 -4.71 0.228 -0.2460 -5.71 0.173 -0.2460 -6.96 0.166 -0.2460 Tabulated from data in file CL00847.DAT & reduced using program Q02.00L Average Reynolds #: 299500 Number of angles of attack: 49 alpha / Cl / Cm -6.35 0.168 -0.2460 -5.18 0.222 -0.2460 -4.26 0.299 -0.2460 -3.30 0.418 -0.2460 -2.38 0.712 -0.2460 -1.35 0.820 -0.2460 -0.30 0.923 -0.2460 0.76 1.027 -0.2460 1.73 1.121 -0.2460 2.75 1.219 -0.2460 3.84 1.319 -0.2460 4.88 1.413 -0.2460 5.86 1.497 -0.2460 6.85 1.579 -0.2460 7.86 1.662 -0.2460 8.92 1.742 -0.2460 10.09 1.827 -0.2460 11.11 1.898 -0.2460 12.11 1.964 -0.2460 13.27 2.019 -0.2460 14.12 2.020 -0.2460 15.14 2.002 -0.2460 16.36 1.985 -0.2460 17.20 1.954 -0.2460 18.32 1.938 -0.2460 16.52 1.964 -0.2460 15.63 1.991 -0.2460 14.58 2.011 -0.2460 13.54 2.021 -0.2460 12.56 1.988 -0.2460 11.63 1.933 -0.2460 10.71 1.869 -0.2460 9.50 1.779 -0.2460 8.67 1.719 -0.2460 7.64 1.636 -0.2460 6.70 1.563 -0.2460 5.60 1.468 -0.2460 4.57 1.378 -0.2460 3.64 1.297 -0.2460 2.67 1.206 -0.2460 1.59 1.102 -0.2460 0.54 0.999 -0.2460 -0.34 0.912 -0.2460 -1.43 0.801 -0.2460 -2.36 0.702 -0.2460 -3.31 0.416 -0.2460 -4.60 0.256 -0.2460 -5.81 0.179 -0.2460 -6.83 0.160 -0.2460 Tabulated from data in file CL00849.DAT & reduced using program Q02.00L File e423.lft created on 09-12-1997 at 13:46:17 using program FORMAT