Airfoil: BW-3 Builder: M. Allen Comment: clean Number of Reynolds #'s: 5 Average Reynolds #: 60000 Number of angles of attack: 49 alpha / Cl / Cm -4.77 -0.259 -0.0074 -3.75 -0.193 -0.0220 -2.71 -0.110 -0.0406 -1.66 -0.020 -0.0605 -0.60 0.116 -0.0746 0.47 0.276 -0.0925 1.50 0.414 -0.1079 2.59 0.586 -0.1155 3.64 0.738 -0.1272 4.67 0.890 -0.1264 5.70 0.985 -0.1248 6.85 1.064 -0.1063 7.41 1.092 -0.0982 8.89 1.179 -0.0918 9.87 1.236 -0.0809 10.84 1.268 -0.0733 11.49 1.298 -0.0653 12.89 1.317 -0.0766 13.84 1.261 -0.1365 14.85 1.207 -0.1679 15.87 1.189 -0.1743 16.87 1.211 -0.1825 17.87 1.196 -0.1852 18.53 1.239 -0.1869 19.51 1.241 -0.1926 17.62 1.225 -0.1880 16.68 1.166 -0.1826 15.67 1.158 -0.1733 14.80 1.221 -0.1666 13.90 1.299 -0.1398 13.00 1.327 -0.0898 11.64 1.318 -0.0766 10.77 1.294 -0.0850 9.91 1.253 -0.0864 8.93 1.204 -0.0953 7.92 1.150 -0.0994 6.53 1.071 -0.1159 5.99 1.040 -0.1244 4.52 0.928 -0.1371 3.54 0.775 -0.1412 2.61 0.616 -0.1302 1.71 0.486 -0.1193 0.37 0.303 -0.1058 -0.51 0.173 -0.0905 -1.50 0.024 -0.0743 -2.43 -0.091 -0.0544 -3.35 -0.178 -0.0339 -4.72 -0.256 -0.0068 -5.64 -0.295 0.0060 Tabulated from data in file PG01722.DAT & reduced using program Q06.01L Average Reynolds #: 100000 Number of angles of attack: 49 alpha / Cl / Cm -5.14 -0.351 0.0208 -3.60 -0.286 -0.0044 -2.49 -0.198 -0.0267 -1.47 -0.036 -0.0563 -0.40 0.151 -0.0876 0.73 0.372 -0.1128 1.86 0.565 -0.1294 2.44 0.651 -0.1353 3.56 0.794 -0.1360 4.68 0.893 -0.1276 5.82 0.987 -0.1176 6.46 1.036 -0.1125 7.54 1.102 -0.1036 8.61 1.166 -0.0964 9.67 1.233 -0.0904 10.72 1.291 -0.0836 11.75 1.327 -0.0775 12.80 1.350 -0.0803 13.80 1.343 -0.1492 14.79 1.178 -0.1793 15.38 1.174 -0.1859 17.06 1.149 -0.1903 17.66 1.156 -0.1924 18.82 1.165 -0.1946 19.96 1.193 -0.1980 17.83 1.172 -0.1976 16.74 1.144 -0.1920 15.71 1.140 -0.1859 14.71 1.216 -0.1848 13.83 1.333 -0.1495 12.87 1.355 -0.0922 11.94 1.335 -0.0843 10.97 1.303 -0.0882 9.56 1.229 -0.0966 9.00 1.193 -0.1005 7.53 1.104 -0.1099 6.94 1.074 -0.1161 5.91 0.998 -0.1259 4.87 0.916 -0.1349 3.83 0.831 -0.1440 2.80 0.711 -0.1468 1.79 0.558 -0.1382 0.29 0.288 -0.1108 -0.25 0.181 -0.0985 -1.79 -0.098 -0.0547 -2.74 -0.215 -0.0301 -3.68 -0.279 -0.0093 -4.61 -0.330 0.0083 -5.55 -0.358 0.0193 Tabulated from data in file PG01514.DAT & reduced using program Q06.01L Average Reynolds #: 200100 Number of angles of attack: 49 alpha / Cl / Cm -4.77 -0.335 0.0109 -3.70 -0.277 -0.0082 -2.73 -0.116 -0.0491 -1.56 0.126 -0.0947 -0.48 0.368 -0.1265 0.45 0.529 -0.1375 1.55 0.656 -0.1352 2.67 0.769 -0.1317 3.84 0.885 -0.1269 4.59 0.959 -0.1246 5.88 1.065 -0.1172 6.56 1.107 -0.1126 7.82 1.193 -0.1046 8.53 1.241 -0.1012 9.72 1.310 -0.0932 10.79 1.361 -0.0860 11.84 1.413 -0.0882 12.73 1.389 -0.1314 13.67 1.333 -0.1759 14.59 1.240 -0.1950 15.59 1.206 -0.1991 16.63 1.191 -0.2008 17.63 1.182 -0.2011 18.64 1.207 -0.2036 19.69 1.201 -0.2039 17.54 1.182 -0.2013 16.85 1.178 -0.2008 15.79 1.174 -0.1969 14.70 1.234 -0.1967 13.67 1.321 -0.1783 13.16 1.363 -0.1609 11.86 1.413 -0.0921 10.83 1.363 -0.0893 9.78 1.313 -0.0959 8.71 1.250 -0.1025 7.60 1.175 -0.1087 6.45 1.099 -0.1155 5.71 1.058 -0.1211 4.47 0.949 -0.1269 3.72 0.877 -0.1303 2.45 0.753 -0.1349 1.75 0.682 -0.1375 0.62 0.561 -0.1411 -0.31 0.401 -0.1335 -1.38 0.182 -0.1052 -2.51 -0.055 -0.0638 -3.51 -0.246 -0.0198 -4.53 -0.322 0.0029 -5.53 -0.373 0.0190 Tabulated from data in file PG01516.DAT & reduced using program Q06.01L Average Reynolds #: 299500 Number of angles of attack: 37 alpha / Cl / Cm -2.99 -0.075 -0.0614 -1.78 0.169 -0.1043 -0.50 0.417 -0.1286 0.30 0.521 -0.1303 1.60 0.670 -0.1288 2.45 0.763 -0.1273 3.78 0.903 -0.1254 4.65 0.988 -0.1224 5.62 1.059 -0.1175 6.67 1.135 -0.1120 7.63 1.207 -0.1074 8.66 1.279 -0.1017 9.78 1.342 -0.0940 10.90 1.407 -0.0873 12.01 1.440 -0.0917 12.70 1.418 -0.1227 13.31 1.380 -0.1560 14.42 1.313 -0.1889 15.49 1.242 -0.1991 14.07 1.326 -0.1809 13.11 1.393 -0.1486 11.72 1.443 -0.0903 10.68 1.390 -0.0901 10.06 1.355 -0.0927 8.82 1.288 -0.1015 7.61 1.204 -0.1076 6.94 1.154 -0.1111 5.81 1.071 -0.1170 4.70 0.990 -0.1232 3.67 0.890 -0.1268 2.66 0.783 -0.1294 1.68 0.676 -0.1316 0.78 0.574 -0.1325 -0.21 0.457 -0.1316 -1.47 0.252 -0.1168 -2.18 0.086 -0.0931 -3.45 -0.166 -0.0417 Tabulated from data in file PG01518.DAT & reduced using program Q06.01L Average Reynolds #: 399300 Number of angles of attack: 33 alpha / Cl / Cm -3.07 -0.038 -0.0707 -1.95 0.217 -0.1131 -0.76 0.405 -0.1263 0.39 0.554 -0.1293 1.44 0.677 -0.1286 2.51 0.796 -0.1274 3.39 0.889 -0.1260 4.39 0.984 -0.1228 5.53 1.069 -0.1169 6.68 1.160 -0.1125 7.54 1.224 -0.1077 8.86 1.312 -0.1001 9.80 1.365 -0.0937 10.75 1.431 -0.0890 11.66 1.441 -0.0924 12.33 1.421 -0.1238 13.31 1.401 -0.1636 12.19 1.430 -0.1159 10.67 1.420 -0.0889 9.49 1.344 -0.0924 8.84 1.308 -0.0966 7.70 1.230 -0.1040 6.64 1.150 -0.1096 5.55 1.064 -0.1143 4.52 0.989 -0.1200 3.60 0.904 -0.1235 2.70 0.810 -0.1259 1.88 0.720 -0.1275 0.68 0.582 -0.1289 -0.41 0.445 -0.1278 -1.42 0.309 -0.1221 -2.27 0.143 -0.1034 -3.32 -0.099 -0.0574 Tabulated from data in file PG01520.DAT & reduced using program Q06.01L File BW3.LFT created on 10-24-1997 at 19:34:41 using program FORMAT