Airfoil: RG15 (C) Builder: B. Champine Comment: flap = 15 degs Number of Reynolds #'s: 2 Average Reynolds #: 100300 Number of angles of attack: 49 alpha / Cl / Cm -6.32 0.124 -0.1373 -4.75 0.299 -0.1442 -4.17 0.345 -0.1401 -2.66 0.437 -0.1233 -2.09 0.505 -0.1252 -1.05 0.609 -0.1257 -0.04 0.694 -0.1247 1.45 0.915 -0.1430 2.01 1.016 -0.1494 3.50 1.106 -0.1315 4.03 1.124 -0.1256 5.07 1.158 -0.1155 6.06 1.212 -0.1086 7.09 1.270 -0.1015 8.09 1.322 -0.0957 9.56 1.390 -0.1127 10.06 1.371 -0.1376 11.44 1.292 -0.1989 12.35 1.183 -0.2044 13.36 1.178 -0.2109 14.35 1.177 -0.2143 15.37 1.149 -0.2123 16.44 1.169 -0.2194 17.49 1.190 -0.2263 18.04 1.235 -0.2360 16.20 1.143 -0.2183 15.28 1.144 -0.2180 14.30 1.152 -0.2160 13.36 1.186 -0.2181 12.47 1.230 -0.2159 11.16 1.284 -0.1972 10.29 1.331 -0.1610 9.45 1.344 -0.1154 8.61 1.342 -0.1019 7.25 1.284 -0.1058 6.32 1.232 -0.1121 5.38 1.189 -0.1202 4.47 1.143 -0.1254 3.50 1.108 -0.1368 2.13 1.038 -0.1543 1.15 0.859 -0.1427 0.25 0.743 -0.1309 -0.65 0.667 -0.1288 -1.60 0.588 -0.1318 -2.93 0.439 -0.1288 -3.85 0.386 -0.1402 -4.80 0.311 -0.1485 -5.79 0.218 -0.1496 -6.80 0.055 -0.1353 Tabulated from data in file MS01738.DAT & reduced using program Q06.01L Average Reynolds #: 200300 Number of angles of attack: 49 alpha / Cl / Cm -6.25 0.104 -0.1359 -5.12 0.238 -0.1444 -3.99 0.352 -0.1453 -2.81 0.446 -0.1365 -1.68 0.547 -0.1327 -1.05 0.599 -0.1307 0.03 0.788 -0.1467 1.16 1.015 -0.1609 2.26 1.037 -0.1405 3.39 1.063 -0.1253 4.45 1.125 -0.1180 5.04 1.159 -0.1147 6.10 1.225 -0.1086 7.17 1.287 -0.1031 8.16 1.333 -0.0981 9.19 1.392 -0.0984 10.46 1.372 -0.1564 11.27 1.339 -0.1940 12.14 1.329 -0.2097 13.53 1.281 -0.2209 13.99 1.275 -0.2231 15.43 1.270 -0.2210 16.32 1.286 -0.2254 17.20 1.292 -0.2298 18.47 1.254 -0.2455 15.98 1.260 -0.2238 15.45 1.281 -0.2268 14.41 1.266 -0.2226 12.94 1.306 -0.2176 12.38 1.308 -0.2165 11.48 1.343 -0.1976 10.10 1.406 -0.1494 9.62 1.368 -0.1264 8.27 1.339 -0.0986 7.35 1.298 -0.1035 6.36 1.242 -0.1092 5.37 1.182 -0.1149 4.35 1.123 -0.1209 3.26 1.061 -0.1275 2.15 1.049 -0.1433 1.46 1.043 -0.1569 0.34 0.872 -0.1549 -0.74 0.646 -0.1340 -1.77 0.538 -0.1327 -2.89 0.435 -0.1367 -4.13 0.339 -0.1465 -4.76 0.277 -0.1464 -5.93 0.138 -0.1377 -7.12 -0.004 -0.1304 Tabulated from data in file MS01737.DAT & reduced using program Q06.01L File RG15C15.LFT created on 10-24-1997 at 19:34:41 using program FORMAT