Airfoil: DU 86-084/18 Builder: R. Adams Comment: clean Number of Reynolds #'s: 4 Average Reynolds #: 60200 Number of angles of attack: 49 alpha / Cl / Cm -5.90 -0.407 -0.0260 -4.46 -0.333 -0.0260 -3.46 -0.272 -0.0260 -2.42 -0.197 -0.0260 -1.35 -0.118 -0.0260 -0.35 -0.042 -0.0260 0.67 0.058 -0.0260 1.69 0.152 -0.0260 2.73 0.290 -0.0260 3.79 0.473 -0.0260 4.84 0.567 -0.0260 5.85 0.638 -0.0260 6.67 0.691 -0.0260 7.82 0.755 -0.0260 8.91 0.814 -0.0260 9.78 0.860 -0.0260 10.87 0.896 -0.0260 11.72 0.905 -0.0260 12.84 0.899 -0.0260 13.69 0.824 -0.0260 14.81 0.832 -0.0260 15.94 0.857 -0.0260 16.87 0.833 -0.0260 17.97 0.824 -0.0260 18.82 0.821 -0.0260 17.30 0.848 -0.0260 16.35 0.854 -0.0260 15.28 0.883 -0.0260 14.33 0.890 -0.0260 13.37 0.886 -0.0260 12.36 0.901 -0.0260 11.46 0.954 -0.0260 10.39 0.923 -0.0260 9.45 0.883 -0.0260 8.36 0.820 -0.0260 7.40 0.760 -0.0260 6.29 0.701 -0.0260 5.34 0.609 -0.0260 4.25 0.549 -0.0260 3.18 0.389 -0.0260 2.31 0.249 -0.0260 1.24 0.137 -0.0260 0.18 0.037 -0.0260 -0.89 -0.056 -0.0260 -1.97 -0.131 -0.0260 -2.84 -0.214 -0.0260 -3.91 -0.280 -0.0260 -4.97 -0.340 -0.0260 -5.91 -0.393 -0.0260 Tabulated from data in file CL00789.DAT & reduced using program Q02.00L Average Reynolds #: 100600 Number of angles of attack: 49 alpha / Cl / Cm -5.96 -0.460 -0.0260 -4.46 -0.364 -0.0260 -3.38 -0.281 -0.0260 -2.54 -0.215 -0.0260 -1.43 -0.128 -0.0260 -0.33 -0.020 -0.0260 0.68 0.108 -0.0260 1.79 0.249 -0.0260 2.62 0.380 -0.0260 3.75 0.496 -0.0260 4.85 0.577 -0.0260 5.69 0.639 -0.0260 6.88 0.729 -0.0260 7.75 0.789 -0.0260 8.92 0.863 -0.0260 9.77 0.906 -0.0260 10.85 0.950 -0.0260 11.82 0.970 -0.0260 12.91 0.914 -0.0260 13.77 0.883 -0.0260 14.89 0.872 -0.0260 15.91 0.870 -0.0260 16.95 0.862 -0.0260 17.81 0.854 -0.0260 18.98 0.867 -0.0260 17.26 0.845 -0.0260 16.25 0.868 -0.0260 15.35 0.909 -0.0260 14.37 0.869 -0.0260 13.35 0.918 -0.0260 12.41 0.952 -0.0260 11.28 0.955 -0.0260 10.33 0.942 -0.0260 9.44 0.893 -0.0260 8.38 0.835 -0.0260 7.43 0.769 -0.0260 6.29 0.692 -0.0260 5.32 0.618 -0.0260 4.20 0.534 -0.0260 3.29 0.459 -0.0260 2.17 0.313 -0.0260 1.04 0.152 -0.0260 0.08 0.041 -0.0260 -0.85 -0.071 -0.0260 -1.86 -0.164 -0.0260 -2.96 -0.231 -0.0260 -4.02 -0.321 -0.0260 -4.92 -0.383 -0.0260 -5.99 -0.442 -0.0260 Tabulated from data in file CL00791.DAT & reduced using program Q02.00L Average Reynolds #: 201300 Number of angles of attack: 49 alpha / Cl / Cm -5.89 -0.410 -0.0260 -4.44 -0.269 -0.0260 -3.30 -0.159 -0.0260 -2.37 -0.075 -0.0260 -1.42 -0.005 -0.0260 -0.20 0.113 -0.0260 0.70 0.238 -0.0260 1.61 0.313 -0.0260 2.69 0.395 -0.0260 3.79 0.481 -0.0260 4.69 0.572 -0.0260 5.81 0.670 -0.0260 6.93 0.759 -0.0260 7.83 0.826 -0.0260 8.89 0.895 -0.0260 9.79 0.953 -0.0260 10.89 0.992 -0.0260 11.89 1.003 -0.0260 12.98 0.984 -0.0260 13.67 0.925 -0.0260 14.76 0.922 -0.0260 15.84 0.889 -0.0260 16.92 0.882 -0.0260 17.93 0.868 -0.0260 18.97 0.876 -0.0260 17.29 0.866 -0.0260 16.14 0.884 -0.0260 15.17 0.903 -0.0260 14.39 0.927 -0.0260 13.27 0.942 -0.0260 12.25 0.989 -0.0260 11.43 0.998 -0.0260 10.37 0.983 -0.0260 9.34 0.916 -0.0260 8.36 0.854 -0.0260 7.36 0.783 -0.0260 6.35 0.704 -0.0260 5.15 0.600 -0.0260 4.14 0.507 -0.0260 3.28 0.428 -0.0260 2.15 0.343 -0.0260 1.11 0.264 -0.0260 0.05 0.160 -0.0260 -1.06 0.009 -0.0260 -1.92 -0.059 -0.0260 -3.02 -0.143 -0.0260 -3.88 -0.221 -0.0260 -5.09 -0.337 -0.0260 -5.95 -0.417 -0.0260 Tabulated from data in file CL00793.DAT & reduced using program Q02.00L Average Reynolds #: 301600 Number of angles of attack: 49 alpha / Cl / Cm -6.41 -0.474 -0.0260 -4.12 -0.263 -0.0260 -3.35 -0.188 -0.0260 -2.26 -0.090 -0.0260 -1.15 -0.010 -0.0260 -0.46 0.032 -0.0260 0.85 0.209 -0.0260 1.80 0.297 -0.0260 2.65 0.377 -0.0260 3.92 0.495 -0.0260 4.69 0.564 -0.0260 5.92 0.675 -0.0260 6.80 0.749 -0.0260 7.87 0.835 -0.0260 8.91 0.905 -0.0260 9.73 0.966 -0.0260 10.74 1.010 -0.0260 11.72 1.013 -0.0260 12.65 1.013 -0.0260 13.83 0.961 -0.0260 14.89 0.910 -0.0260 15.78 0.894 -0.0260 16.81 0.868 -0.0260 17.74 0.857 -0.0260 18.88 0.868 -0.0260 17.26 0.869 -0.0260 16.18 0.878 -0.0260 15.35 0.892 -0.0260 14.31 0.936 -0.0260 13.21 0.987 -0.0260 12.41 1.013 -0.0260 11.33 1.017 -0.0260 10.40 0.995 -0.0260 9.30 0.929 -0.0260 8.43 0.871 -0.0260 7.25 0.784 -0.0260 6.22 0.697 -0.0260 5.18 0.604 -0.0260 4.14 0.510 -0.0260 3.11 0.413 -0.0260 2.06 0.317 -0.0260 1.17 0.238 -0.0260 0.16 0.102 -0.0260 -0.99 -0.008 -0.0260 -1.95 -0.067 -0.0260 -3.24 -0.179 -0.0260 -3.96 -0.249 -0.0260 -5.22 -0.365 -0.0260 -5.98 -0.432 -0.0260 Tabulated from data in file CL00795.DAT & reduced using program Q02.00L File du86.lft created on 09-12-1997 at 13:46:17 using program FORMAT