Airfoil: W1011-20 fp20 Builder: S. Cassidy Comment: Clean, Cf/C = 20%, Flap = 20° Number of Reynolds #'s: 3 Average Reynolds #: 99889.4 Number of angles of attack: 45 alpha / Cl / Cm -10.27 -0.41 -0.1236 -9.32 -0.31 -0.1283 -8.34 -0.22 -0.1290 -7.22 -0.12 -0.1298 -6.23 -0.03 -0.1278 -5.17 0.06 -0.1258 -4.15 0.14 -0.1199 -3.25 0.22 -0.1154 -2.24 0.32 -0.1172 -0.99 0.45 -0.1202 -0.20 0.54 -0.1295 0.92 0.70 -0.1300 2.03 0.73 -0.1165 2.89 0.80 -0.1144 4.09 0.90 -0.1119 5.13 0.97 -0.1080 6.03 1.04 -0.1058 7.12 1.12 -0.1033 8.03 1.15 -0.1948 8.94 1.01 -0.2177 9.85 1.00 -0.2305 10.93 0.96 -0.2286 11.96 0.98 -0.2322 11.73 1.02 -0.2217 10.66 0.99 -0.2124 9.71 1.06 -0.2123 8.79 1.04 -0.1884 7.86 1.20 -0.0972 6.72 1.12 -0.0975 5.91 1.06 -0.0994 4.87 0.99 -0.1029 3.64 0.89 -0.1056 2.70 0.81 -0.1073 1.63 0.73 -0.1110 0.80 0.72 -0.1238 -0.35 0.56 -0.1149 -1.34 0.44 -0.1092 -2.44 0.34 -0.1090 -3.35 0.25 -0.1090 -4.52 0.15 -0.1147 -5.43 0.08 -0.1197 -6.46 -0.02 -0.1233 -7.57 -0.12 -0.1258 -8.42 -0.20 -0.1262 -9.52 -0.30 -0.1253 Tabulated from data in file 07096gw.dat & reduced using program C10.20 Average Reynolds #: 199936.0 Number of angles of attack: 47 alpha / Cl / Cm -10.46 -0.36 -0.1337 -9.32 -0.25 -0.1370 -8.37 -0.15 -0.1375 -7.37 -0.05 -0.1386 -6.20 0.06 -0.1383 -5.30 0.14 -0.1373 -4.13 0.26 -0.1384 -3.21 0.36 -0.1384 -2.09 0.46 -0.1367 -1.03 0.59 -0.1408 -0.10 0.72 -0.1453 1.02 0.74 -0.1252 2.05 0.81 -0.1195 2.95 0.89 -0.1174 3.94 0.97 -0.1146 5.01 1.06 -0.1116 6.03 1.14 -0.1095 7.11 1.23 -0.1071 8.17 1.31 -0.1053 8.89 1.23 -0.2040 9.99 1.13 -0.2267 10.93 1.12 -0.2324 11.85 1.11 -0.2350 12.97 1.09 -0.2358 12.74 1.09 -0.2281 11.74 1.11 -0.2284 10.71 1.11 -0.2242 9.74 1.16 -0.2202 9.01 1.35 -0.0970 7.90 1.29 -0.1010 6.93 1.22 -0.1023 5.72 1.13 -0.1051 4.81 1.05 -0.1074 3.66 0.96 -0.1104 2.69 0.88 -0.1133 1.66 0.79 -0.1164 0.67 0.73 -0.1245 -0.39 0.74 -0.1494 -1.38 0.55 -0.1327 -2.46 0.43 -0.1319 -3.39 0.33 -0.1336 -4.37 0.24 -0.1344 -5.51 0.13 -0.1335 -6.56 0.03 -0.1339 -7.45 -0.06 -0.1347 -8.45 -0.16 -0.1343 -9.62 -0.28 -0.1330 Tabulated from data in file 07098gw.dat & reduced using program C10.20 Average Reynolds #: 400055.6 Number of angles of attack: 43 alpha / Cl / Cm -10.25 -0.34 -0.1366 -9.29 -0.24 -0.1390 -8.24 -0.13 -0.1400 -7.19 -0.03 -0.1414 -6.27 0.06 -0.1417 -5.32 0.16 -0.1414 -4.16 0.27 -0.1422 -3.09 0.37 -0.1413 -2.22 0.48 -0.1466 -1.07 0.72 -0.1662 -0.05 0.73 -0.1476 0.87 0.79 -0.1423 1.93 0.86 -0.1335 2.92 0.92 -0.1266 3.93 1.00 -0.1198 4.97 1.08 -0.1167 6.03 1.18 -0.1140 7.04 1.25 -0.1103 8.17 1.35 -0.1073 9.21 1.42 -0.1034 10.23 1.47 -0.1005 11.11 1.44 -0.1139 11.02 1.48 -0.0984 9.82 1.46 -0.1009 8.77 1.38 -0.1032 7.80 1.32 -0.1070 6.94 1.25 -0.1097 5.91 1.17 -0.1122 4.87 1.08 -0.1154 3.77 0.99 -0.1193 2.74 0.91 -0.1260 1.62 0.84 -0.1328 0.61 0.77 -0.1403 -0.32 0.73 -0.1496 -1.47 0.64 -0.1582 -2.44 0.44 -0.1414 -3.49 0.34 -0.1394 -4.39 0.25 -0.1398 -5.53 0.14 -0.1399 -6.39 0.05 -0.1395 -7.59 -0.07 -0.1390 -8.55 -0.17 -0.1375 -9.57 -0.27 -0.1375 Tabulated from data in file 07100gw.dat & reduced using program C10.20 File w1011-20_fp20_lift.dat created using program clcm dist V1.1 on 30-Mar-2012 09:46:57