Airfoil: W1015-30 fp15 Builder: S. Cassidy Comment: Clean, Cf/C = 30%, Flap = 15° Number of Reynolds #'s: 3 Average Reynolds #: 100045.8 Number of angles of attack: 53 alpha / Cl / Cm -10.42 -0.34 -0.1158 -9.36 -0.28 -0.1147 -8.35 -0.21 -0.1115 -7.29 -0.13 -0.1085 -6.13 -0.04 -0.1064 -5.17 0.04 -0.1038 -4.07 0.13 -0.1014 -3.06 0.21 -0.0970 -2.05 0.29 -0.0956 -1.15 0.33 -0.0940 0.00 0.54 -0.1139 0.90 0.73 -0.1266 1.92 0.86 -0.1203 3.14 0.89 -0.1089 4.12 0.94 -0.1043 5.15 1.00 -0.0974 6.01 1.05 -0.0931 7.20 1.12 -0.0867 8.12 1.17 -0.0828 9.21 1.22 -0.0769 10.22 1.28 -0.0756 11.12 1.32 -0.0727 11.93 0.92 -0.1875 13.00 0.96 -0.1912 14.02 0.96 -0.1897 14.89 0.99 -0.1955 15.98 1.02 -0.2016 15.73 0.99 -0.1870 14.83 1.01 -0.1835 13.83 0.99 -0.1800 12.76 0.93 -0.1698 11.60 0.90 -0.1619 10.82 0.90 -0.1562 9.71 0.90 -0.1484 8.80 0.94 -0.1381 7.74 1.19 -0.0806 6.71 1.14 -0.0854 5.73 1.09 -0.0898 4.87 1.03 -0.0945 3.66 0.97 -0.0998 2.71 0.92 -0.1070 1.63 0.89 -0.1168 0.62 0.70 -0.1111 -0.45 0.47 -0.0967 -1.43 0.36 -0.0876 -2.28 0.31 -0.0891 -3.38 0.23 -0.0905 -4.45 0.15 -0.0947 -5.55 0.06 -0.0989 -6.32 -0.01 -0.1022 -7.61 -0.11 -0.1055 -8.55 -0.18 -0.1089 -9.51 -0.25 -0.1119 Tabulated from data in file 07209sn.dat & reduced using program C10.20 Average Reynolds #: 199954.6 Number of angles of attack: 55 alpha / Cl / Cm -10.42 -0.25 -0.1361 -9.32 -0.19 -0.1314 -8.21 -0.13 -0.1257 -7.34 -0.07 -0.1222 -6.24 0.01 -0.1182 -5.20 0.08 -0.1143 -4.13 0.17 -0.1122 -3.10 0.28 -0.1128 -2.08 0.39 -0.1136 -0.97 0.51 -0.1159 -0.11 0.70 -0.1274 0.96 0.87 -0.1274 1.96 0.86 -0.1136 3.06 0.90 -0.1039 3.93 0.95 -0.0988 5.16 1.03 -0.0932 6.07 1.10 -0.0907 7.17 1.19 -0.0877 8.07 1.26 -0.0857 9.24 1.34 -0.0824 10.23 1.42 -0.0804 11.12 1.47 -0.0777 12.20 1.51 -0.0755 13.14 1.52 -0.0803 14.10 1.46 -0.0963 15.11 1.40 -0.1067 15.86 1.03 -0.1927 16.85 1.07 -0.2043 16.68 1.02 -0.1910 15.60 1.04 -0.1872 14.64 1.02 -0.1818 13.81 1.02 -0.1815 12.66 0.98 -0.1748 11.74 0.97 -0.1695 11.06 1.46 -0.0706 9.84 1.39 -0.0746 8.80 1.30 -0.0767 7.88 1.24 -0.0789 6.75 1.16 -0.0820 5.73 1.08 -0.0848 4.69 1.01 -0.0889 3.75 0.94 -0.0929 2.78 0.89 -0.0990 1.83 0.87 -0.1095 0.80 0.87 -0.1228 -0.41 0.64 -0.1180 -1.44 0.46 -0.1082 -2.42 0.35 -0.1067 -3.40 0.25 -0.1069 -4.56 0.15 -0.1090 -5.52 0.07 -0.1106 -6.34 0.01 -0.1151 -7.57 -0.08 -0.1190 -8.49 -0.14 -0.1230 -9.58 -0.20 -0.1285 Tabulated from data in file 07207sn.dat & reduced using program C10.20 Average Reynolds #: 400027.7 Number of angles of attack: 51 alpha / Cl / Cm -10.38 -0.19 -0.1415 -9.36 -0.13 -0.1404 -8.27 -0.06 -0.1345 -7.13 0.02 -0.1308 -6.24 0.09 -0.1281 -5.27 0.17 -0.1262 -4.17 0.27 -0.1249 -3.10 0.38 -0.1255 -2.15 0.54 -0.1353 -1.08 0.77 -0.1457 0.00 0.82 -0.1321 1.04 0.85 -0.1236 1.91 0.89 -0.1162 2.97 0.94 -0.1087 4.09 1.01 -0.1026 5.15 1.08 -0.0979 6.16 1.16 -0.0935 7.05 1.23 -0.0906 8.07 1.31 -0.0855 9.27 1.41 -0.0828 10.20 1.49 -0.0797 11.29 1.57 -0.0775 12.31 1.61 -0.0746 13.13 1.50 -0.0987 14.14 1.44 -0.1081 15.06 1.40 -0.1148 14.90 1.40 -0.1128 13.94 1.47 -0.1053 12.95 1.53 -0.0892 11.87 1.60 -0.0746 10.95 1.55 -0.0765 9.83 1.46 -0.0796 8.85 1.38 -0.0822 7.92 1.31 -0.0851 6.78 1.21 -0.0894 5.77 1.13 -0.0932 4.74 1.06 -0.0979 3.75 0.99 -0.1028 2.67 0.92 -0.1081 1.78 0.88 -0.1155 0.73 0.84 -0.1243 -0.35 0.81 -0.1337 -1.32 0.73 -0.1430 -2.39 0.50 -0.1308 -3.43 0.34 -0.1222 -4.49 0.24 -0.1233 -5.34 0.16 -0.1246 -6.54 0.07 -0.1276 -7.54 -0.01 -0.1312 -8.55 -0.07 -0.1359 -9.63 -0.13 -0.1401 Tabulated from data in file 07205sn.dat & reduced using program C10.20 File w1015-30_fp15_lift.dat created using program clcm dist V1.1 on 30-Mar-2012 09:46:59