Airfoil: A18 Builder: R. Cooney Comment: clean Number of Reynolds #'s: 6 Average Reynolds #: 30500 Number of angles of attack: 49 alpha / Cl / Cm -5.44 -0.361 -0.0800 -4.15 -0.255 -0.0800 -2.90 -0.140 -0.0800 -1.98 -0.062 -0.0800 -1.08 0.021 -0.0800 0.12 0.140 -0.0800 0.95 0.225 -0.0800 2.16 0.329 -0.0800 3.18 0.449 -0.0800 4.03 0.552 -0.0800 5.24 0.697 -0.0800 6.34 0.863 -0.0800 7.17 0.961 -0.0800 8.34 1.037 -0.0800 9.23 1.082 -0.0800 10.40 1.086 -0.0800 11.23 1.032 -0.0800 12.37 1.028 -0.0800 13.18 0.928 -0.0800 14.28 0.834 -0.0800 15.09 0.843 -0.0800 16.23 0.878 -0.0800 17.40 0.990 -0.0800 18.28 1.078 -0.0800 19.18 0.998 -0.0800 17.75 0.989 -0.0800 16.86 0.926 -0.0800 15.79 0.877 -0.0800 14.75 0.877 -0.0800 13.89 0.854 -0.0800 12.87 0.904 -0.0800 11.88 1.083 -0.0800 10.86 1.124 -0.0800 10.03 1.103 -0.0800 9.01 1.058 -0.0800 7.94 1.003 -0.0800 6.97 0.960 -0.0800 5.96 0.827 -0.0800 4.90 0.710 -0.0800 3.87 0.562 -0.0800 2.85 0.452 -0.0800 1.77 0.348 -0.0800 0.78 0.267 -0.0800 -0.27 0.161 -0.0800 -1.42 0.040 -0.0800 -2.28 -0.040 -0.0800 -3.43 -0.143 -0.0800 -4.43 -0.244 -0.0800 -5.36 -0.335 -0.0800 Tabulated from data in file AB00520.DAT & reduced using program Q01.00L Average Reynolds #: 40300 Number of angles of attack: 49 alpha / Cl / Cm -5.15 -0.328 -0.0800 -4.08 -0.216 -0.0800 -2.95 -0.109 -0.0800 -2.15 -0.040 -0.0800 -1.00 0.064 -0.0800 0.09 0.176 -0.0800 1.09 0.271 -0.0800 2.12 0.396 -0.0800 3.20 0.532 -0.0800 4.19 0.687 -0.0800 5.27 0.819 -0.0800 6.34 0.921 -0.0800 7.32 0.986 -0.0800 8.35 1.026 -0.0800 9.33 1.070 -0.0800 10.14 1.093 -0.0800 11.20 1.132 -0.0800 12.26 1.096 -0.0800 13.28 0.981 -0.0800 14.25 0.899 -0.0800 15.27 0.903 -0.0800 16.30 0.916 -0.0800 17.29 0.951 -0.0800 18.37 0.971 -0.0800 19.16 1.029 -0.0800 17.80 0.981 -0.0800 16.82 0.950 -0.0800 15.84 0.913 -0.0800 14.87 0.921 -0.0800 13.93 0.907 -0.0800 12.86 0.957 -0.0800 11.97 1.142 -0.0800 10.92 1.137 -0.0800 9.98 1.105 -0.0800 8.95 1.076 -0.0800 7.91 1.038 -0.0800 6.89 0.976 -0.0800 5.83 0.905 -0.0800 4.78 0.799 -0.0800 3.81 0.673 -0.0800 2.82 0.511 -0.0800 1.80 0.384 -0.0800 0.64 0.266 -0.0800 -0.39 0.167 -0.0800 -1.42 0.062 -0.0800 -2.34 -0.021 -0.0800 -3.36 -0.112 -0.0800 -4.44 -0.218 -0.0800 -5.44 -0.310 -0.0800 Tabulated from data in file AB00519.DAT & reduced using program Q01.00L Average Reynolds #: 61000 Number of angles of attack: 33 alpha / Cl / Cm -5.24 -0.278 -0.0800 -3.34 -0.084 -0.0800 -2.01 0.030 -0.0800 -0.11 0.225 -0.0800 1.24 0.411 -0.0800 2.49 0.585 -0.0800 4.10 0.788 -0.0800 5.98 0.942 -0.0800 7.17 1.018 -0.0800 9.09 1.115 -0.0800 10.35 1.165 -0.0800 12.13 1.175 -0.0800 13.35 1.138 -0.0800 15.04 1.195 -0.0800 16.23 1.029 -0.0800 18.07 1.069 -0.0800 19.25 1.038 -0.0800 16.99 1.020 -0.0800 15.86 1.067 -0.0800 14.17 1.163 -0.0800 13.02 1.119 -0.0800 11.02 1.164 -0.0800 9.89 1.133 -0.0800 8.24 1.049 -0.0800 6.62 0.969 -0.0800 5.42 0.881 -0.0800 3.67 0.723 -0.0800 1.91 0.485 -0.0800 0.79 0.330 -0.0800 -0.73 0.142 -0.0800 -2.34 -0.006 -0.0800 -3.83 -0.133 -0.0800 -5.45 -0.303 -0.0800 Tabulated from data in file JG00160.DAT & reduced using program Q01.00L Average Reynolds #: 101700 Number of angles of attack: 33 alpha / Cl / Cm -5.36 -0.326 -0.0800 -3.51 -0.101 -0.0800 -1.61 0.093 -0.0800 -0.41 0.268 -0.0800 1.19 0.484 -0.0800 2.81 0.656 -0.0800 4.42 0.800 -0.0800 5.92 0.926 -0.0800 7.53 1.022 -0.0800 9.05 1.110 -0.0800 10.23 1.147 -0.0800 11.96 1.163 -0.0800 13.04 1.143 -0.0800 14.70 1.125 -0.0800 16.43 1.103 -0.0800 17.98 0.940 -0.0800 19.24 1.002 -0.0800 17.05 0.961 -0.0800 15.95 1.123 -0.0800 14.47 1.128 -0.0800 12.87 1.151 -0.0800 11.34 1.151 -0.0800 9.89 1.121 -0.0800 8.27 1.045 -0.0800 6.69 0.954 -0.0800 5.15 0.842 -0.0800 3.70 0.718 -0.0800 2.19 0.577 -0.0800 0.69 0.401 -0.0800 -0.75 0.202 -0.0800 -2.41 -0.018 -0.0800 -3.79 -0.144 -0.0800 -5.45 -0.341 -0.0800 Tabulated from data in file MS00162.DAT & reduced using program Q01.00L Average Reynolds #: 202700 Number of angles of attack: 33 alpha / Cl / Cm -5.40 -0.344 -0.0800 -3.56 -0.060 -0.0800 -1.46 0.209 -0.0800 0.08 0.374 -0.0800 1.49 0.519 -0.0800 2.86 0.656 -0.0800 4.31 0.794 -0.0800 5.63 0.899 -0.0800 7.57 1.039 -0.0800 8.88 1.118 -0.0800 10.12 1.168 -0.0800 11.88 1.184 -0.0800 13.33 1.212 -0.0800 14.88 1.180 -0.0800 16.51 1.141 -0.0800 17.60 1.181 -0.0800 19.11 1.102 -0.0800 17.14 1.187 -0.0800 15.79 1.186 -0.0800 14.17 1.194 -0.0800 12.61 1.223 -0.0800 11.27 1.181 -0.0800 9.81 1.157 -0.0800 8.19 1.072 -0.0800 6.51 0.953 -0.0800 5.30 0.865 -0.0800 3.38 0.697 -0.0800 2.08 0.570 -0.0800 0.63 0.424 -0.0800 -1.30 0.219 -0.0800 -2.68 0.037 -0.0800 -3.95 -0.120 -0.0800 -5.82 -0.397 -0.0800 Tabulated from data in file MS00164.DAT & reduced using program Q01.00L Average Reynolds #: 303200 Number of angles of attack: 33 alpha / Cl / Cm -5.37 -0.255 -0.0800 -3.59 -0.010 -0.0800 -2.33 0.132 -0.0800 -0.50 0.321 -0.0800 1.00 0.476 -0.0800 2.34 0.607 -0.0800 4.45 0.799 -0.0800 5.73 0.895 -0.0800 7.88 1.059 -0.0800 9.39 1.151 -0.0800 10.20 1.181 -0.0800 11.99 1.197 -0.0800 13.33 1.228 -0.0800 14.49 1.221 -0.0800 16.01 1.193 -0.0800 17.28 1.180 -0.0800 18.86 1.100 -0.0800 17.40 1.182 -0.0800 15.80 1.181 -0.0800 14.40 1.222 -0.0800 13.12 1.200 -0.0800 11.15 1.196 -0.0800 9.87 1.166 -0.0800 8.19 1.076 -0.0800 6.27 0.936 -0.0800 4.70 0.814 -0.0800 3.35 0.696 -0.0800 2.05 0.571 -0.0800 0.23 0.380 -0.0800 -0.90 0.266 -0.0800 -2.42 0.109 -0.0800 -3.99 -0.072 -0.0800 -5.34 -0.281 -0.0800 Tabulated from data in file MS00166.DAT & reduced using program Q01.00L File a18.lft created on 12-05-1997 at 15:25:49 using program FORMAT