XFOIL Version 6.96 Calculated polar for: Bergey BW-3 (smoothed) 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.000 -0.4355 0.12038 0.11859 -0.0085 1.0000 0.0095 -9.750 -0.4366 0.11551 0.11372 -0.0099 1.0000 0.0098 -9.500 -0.4343 0.11197 0.11019 -0.0108 1.0000 0.0100 -9.250 -0.4293 0.10937 0.10759 -0.0114 1.0000 0.0101 -9.000 -0.4227 0.10728 0.10552 -0.0117 1.0000 0.0103 -8.750 -0.4081 0.10443 0.10267 -0.0146 0.9993 0.0104 -8.250 -0.3792 0.09804 0.09628 -0.0213 0.9970 0.0110 -6.750 -0.2524 0.02868 0.02574 -0.1061 0.9280 0.0159 -6.500 -0.2076 0.02260 0.01924 -0.1144 0.9221 0.0166 -6.250 -0.1639 0.01820 0.01444 -0.1206 0.9158 0.0172 -6.000 -0.1211 0.01469 0.01051 -0.1258 0.9076 0.0179 -5.750 -0.0765 0.01253 0.00802 -0.1306 0.8978 0.0185 -5.500 -0.0338 0.01128 0.00654 -0.1345 0.8875 0.0191 -5.250 0.0036 0.01066 0.00574 -0.1369 0.8758 0.0195 -5.000 0.0335 0.01010 0.00502 -0.1374 0.8638 0.0204 -4.750 0.0610 0.00969 0.00451 -0.1373 0.8535 0.0213 -4.500 0.0884 0.00941 0.00413 -0.1371 0.8441 0.0221 -4.250 0.1152 0.00916 0.00379 -0.1367 0.8353 0.0229 -4.000 0.1422 0.00897 0.00350 -0.1363 0.8273 0.0237 -3.750 0.1687 0.00867 0.00316 -0.1359 0.8191 0.0254 -3.500 0.1954 0.00848 0.00290 -0.1355 0.8111 0.0270 -3.250 0.2224 0.00832 0.00268 -0.1351 0.8034 0.0282 -2.750 0.2762 0.00798 0.00226 -0.1343 0.7879 0.0327 -2.500 0.3031 0.00787 0.00209 -0.1339 0.7794 0.0353 -2.250 0.3302 0.00772 0.00193 -0.1335 0.7713 0.0408 -2.000 0.3568 0.00763 0.00181 -0.1330 0.7604 0.0479 -1.750 0.3832 0.00760 0.00176 -0.1325 0.7460 0.0548 -1.500 0.4097 0.00762 0.00175 -0.1320 0.7306 0.0597 -1.250 0.4365 0.00764 0.00174 -0.1315 0.7183 0.0640 -1.000 0.4635 0.00765 0.00170 -0.1311 0.7082 0.0659 -0.750 0.4905 0.00768 0.00173 -0.1307 0.6974 0.0689 -0.500 0.5176 0.00772 0.00175 -0.1303 0.6870 0.0711 -0.250 0.5446 0.00775 0.00174 -0.1299 0.6769 0.0728 0.000 0.5717 0.00779 0.00176 -0.1296 0.6663 0.0747 0.250 0.5985 0.00787 0.00181 -0.1291 0.6552 0.0759 0.500 0.6252 0.00786 0.00176 -0.1287 0.6395 0.0780 0.750 0.6513 0.00794 0.00176 -0.1281 0.6158 0.0792 1.000 0.6770 0.00806 0.00179 -0.1275 0.5888 0.0805 1.250 0.7023 0.00824 0.00184 -0.1268 0.5533 0.0817 1.500 0.7272 0.00846 0.00190 -0.1260 0.5120 0.0828 1.750 0.7520 0.00872 0.00199 -0.1253 0.4680 0.0840 2.000 0.7750 0.00914 0.00214 -0.1242 0.4025 0.0851 2.250 0.7989 0.00948 0.00227 -0.1233 0.3555 0.0860 2.500 0.8222 0.00986 0.00244 -0.1223 0.3050 0.0868 2.750 0.8456 0.01023 0.00262 -0.1213 0.2588 0.0874 3.000 0.8661 0.01086 0.00289 -0.1198 0.1807 0.0882 3.250 0.8824 0.01189 0.00339 -0.1175 0.0575 0.0901 3.500 0.9077 0.01209 0.00355 -0.1169 0.0476 0.0917 3.750 0.9334 0.01224 0.00372 -0.1163 0.0436 0.0932 4.000 0.9586 0.01245 0.00391 -0.1157 0.0388 0.0950 4.250 0.9843 0.01261 0.00408 -0.1152 0.0365 0.0963 4.500 1.0096 0.01279 0.00427 -0.1146 0.0342 0.0979 4.750 1.0346 0.01300 0.00449 -0.1139 0.0319 0.0995 5.000 1.0595 0.01323 0.00472 -0.1133 0.0301 0.1006 5.250 1.0850 0.01341 0.00493 -0.1127 0.0290 0.1027 5.500 1.1101 0.01362 0.00517 -0.1121 0.0277 0.1059 5.750 1.1349 0.01386 0.00542 -0.1115 0.0262 0.1088 6.000 1.1590 0.01415 0.00573 -0.1107 0.0244 0.1117 6.250 1.1835 0.01440 0.00600 -0.1100 0.0237 0.1140 6.500 1.2080 0.01465 0.00629 -0.1093 0.0231 0.1181 6.750 1.2324 0.01491 0.00660 -0.1087 0.0221 0.1240 7.250 1.2804 0.01551 0.00727 -0.1072 0.0204 0.1464 7.750 1.4612 0.01638 0.00944 -0.1386 0.0178 1.0000 8.000 1.4836 0.01678 0.00987 -0.1376 0.0173 1.0000 8.250 1.5057 0.01719 0.01029 -0.1365 0.0168 1.0000 8.500 1.5276 0.01760 0.01072 -0.1353 0.0163 1.0000 8.750 1.5485 0.01810 0.01123 -0.1340 0.0156 1.0000 9.000 1.5684 0.01869 0.01187 -0.1325 0.0152 1.0000 9.250 1.5894 0.01913 0.01236 -0.1312 0.0149 1.0000 9.500 1.6097 0.01963 0.01290 -0.1299 0.0146 1.0000 9.750 1.6296 0.02015 0.01348 -0.1284 0.0143 1.0000 10.000 1.6489 0.02071 0.01409 -0.1269 0.0140 1.0000 10.250 1.6684 0.02124 0.01467 -0.1254 0.0136 1.0000 10.500 1.6871 0.02181 0.01528 -0.1238 0.0133 1.0000 10.750 1.7052 0.02241 0.01592 -0.1222 0.0130 1.0000 11.000 1.7233 0.02298 0.01652 -0.1205 0.0126 1.0000 11.250 1.7392 0.02370 0.01729 -0.1185 0.0123 1.0000 11.500 1.7516 0.02466 0.01831 -0.1159 0.0119 1.0000 11.750 1.7645 0.02537 0.01909 -0.1133 0.0118 1.0000 12.000 1.7744 0.02605 0.01985 -0.1101 0.0116 1.0000 12.250 1.7824 0.02685 0.02074 -0.1066 0.0115 1.0000 12.500 1.7913 0.02768 0.02165 -0.1034 0.0113 1.0000 12.750 1.7993 0.02860 0.02265 -0.1003 0.0112 1.0000 13.000 1.8074 0.02958 0.02372 -0.0972 0.0110 1.0000 13.250 1.8148 0.03063 0.02486 -0.0943 0.0108 1.0000 13.500 1.8223 0.03173 0.02604 -0.0915 0.0106 1.0000 13.750 1.8289 0.03295 0.02734 -0.0888 0.0104 1.0000 14.000 1.8352 0.03424 0.02873 -0.0862 0.0102 1.0000 14.250 1.8406 0.03570 0.03028 -0.0839 0.0101 1.0000 14.500 1.8449 0.03737 0.03204 -0.0816 0.0100 1.0000 14.750 1.8490 0.03913 0.03389 -0.0797 0.0098 1.0000 15.000 1.8524 0.04104 0.03587 -0.0778 0.0096 1.0000 15.250 1.8539 0.04323 0.03816 -0.0761 0.0095 1.0000 15.500 1.8536 0.04570 0.04074 -0.0745 0.0094 1.0000 15.750 1.8510 0.04851 0.04366 -0.0731 0.0092 1.0000 16.000 1.8458 0.05174 0.04701 -0.0718 0.0091 1.0000 16.250 1.8446 0.05462 0.05002 -0.0709 0.0090 1.0000 16.500 1.8430 0.05763 0.05315 -0.0702 0.0089 1.0000 16.750 1.8374 0.06125 0.05690 -0.0698 0.0089 1.0000 17.000 1.8305 0.06516 0.06095 -0.0696 0.0088 1.0000 17.250 1.8257 0.06894 0.06484 -0.0696 0.0087 1.0000 17.500 1.8157 0.07358 0.06963 -0.0700 0.0087 1.0000 17.750 1.8050 0.07850 0.07468 -0.0708 0.0086 1.0000 18.000 1.7942 0.08363 0.07995 -0.0719 0.0085 1.0000 18.250 1.7808 0.08939 0.08585 -0.0734 0.0085 1.0000 18.500 1.7660 0.09560 0.09221 -0.0754 0.0084 1.0000 18.750 1.7501 0.10212 0.09887 -0.0777 0.0084 1.0000 19.000 1.7311 0.10945 0.10635 -0.0807 0.0084 1.0000 19.250 1.7130 0.11681 0.11386 -0.0839 0.0083 1.0000