XFOIL Version 6.94 Calculated polar for: BE50 (original) 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.500 0.6180 0.00653 0.00175 -0.1060 0.6654 1.0000 1.000 0.6730 0.00686 0.00185 -0.1056 0.6222 1.0000 1.500 0.7274 0.00724 0.00200 -0.1052 0.5718 1.0000 2.000 0.7809 0.00775 0.00221 -0.1047 0.5116 1.0000 2.500 0.8332 0.00842 0.00251 -0.1041 0.4232 1.0000 3.000 0.8856 0.00916 0.00295 -0.1036 0.3729 1.0000 3.500 0.9388 0.00974 0.00344 -0.1032 0.3431 1.0000 4.000 0.9918 0.01030 0.00390 -0.1028 0.3119 1.0000 4.500 1.0449 0.01081 0.00436 -0.1024 0.2787 1.0000 5.000 1.0970 0.01143 0.00482 -0.1020 0.2293 1.0000 5.500 1.1436 0.01284 0.00570 -0.1009 0.1351 1.0000 6.000 1.1824 0.01553 0.00772 -0.0986 0.0177 1.0000 6.500 1.2290 0.01695 0.00936 -0.0969 0.0139 1.0000 7.000 1.2696 0.01905 0.01172 -0.0945 0.0116 1.0000 7.500 1.3001 0.02221 0.01522 -0.0905 0.0107 1.0000 8.000 1.3318 0.02499 0.01829 -0.0868 0.0103 1.0000 8.500 1.3580 0.02873 0.02232 -0.0824 0.0103 1.0000 9.000 1.3835 0.03291 0.02683 -0.0782 0.0102 1.0000 9.500 1.4054 0.03666 0.03095 -0.0739 0.0096 1.0000 10.000 1.4093 0.04237 0.03714 -0.0676 0.0099 1.0000 11.000 1.2018 0.04166 0.03743 -0.0382 0.0100 1.0000 11.500 1.1585 0.05222 0.04836 -0.0358 0.0102 1.0000 12.000 1.0960 0.06275 0.05922 -0.0339 0.0103 1.0000 12.500 1.0712 0.06997 0.06664 -0.0336 0.0114 1.0000 13.000 1.0335 0.07978 0.07678 -0.0376 0.0117 1.0000 14.000 0.9305 0.10907 0.10684 -0.0546 0.0132 1.0000 14.500 0.8883 0.12432 0.12230 -0.0641 0.0134 1.0000 15.000 1.0822 0.20219 0.20011 -0.1254 0.0210 1.0000 15.500 1.0924 0.21034 0.20825 -0.1297 0.0186 1.0000 16.000 1.1046 0.21511 0.21304 -0.1319 0.0171 1.0000 16.500 1.1068 0.23032 0.22820 -0.1403 0.0157 1.0000 17.000 1.1180 0.24172 0.23957 -0.1469 0.0138 1.0000 17.500 1.1306 0.25046 0.24832 -0.1520 0.0128 1.0000 18.000 1.1446 0.25766 0.25552 -0.1561 0.0119 1.0000 18.500 1.1590 0.26378 0.26165 -0.1594 0.0113 1.0000 19.000 0.8046 0.22698 0.22507 -0.1072 0.0138 1.0000 19.500 0.8101 0.23423 0.23233 -0.1098 0.0127 1.0000 20.000 0.8167 0.24082 0.23893 -0.1121 0.0119 1.0000 20.500 0.8254 0.24665 0.24478 -0.1137 0.0112 1.0000 21.000 0.8288 0.25628 0.25441 -0.1162 0.0108 1.0000 21.500 0.8338 0.26409 0.26222 -0.1190 0.0107 1.0000 22.000 0.8381 0.27184 0.26998 -0.1220 0.0106 1.0000 22.500 0.8419 0.28009 0.27826 -0.1254 0.0098 1.0000 23.000 0.8473 0.28784 0.28602 -0.1280 0.0087 1.0000 23.500 0.8528 0.29518 0.29339 -0.1305 0.0078 1.0000 24.000 0.8582 0.30223 0.30045 -0.1328 0.0073 1.0000 24.500 0.8639 0.30891 0.30715 -0.1349 0.0069 1.0000 25.000 0.8696 0.31798 0.31622 -0.1367 0.0066 1.0000 25.500 0.8735 0.32595 0.32421 -0.1394 0.0066 1.0000 26.000 0.8766 0.33401 0.33228 -0.1423 0.0065 1.0000 26.500 0.8801 0.34208 0.34037 -0.1452 0.0063 1.0000 27.000 0.8843 0.35025 0.34855 -0.1478 0.0059 1.0000 27.500 0.8883 0.35816 0.35650 -0.1503 0.0056 1.0000 28.000 0.8919 0.36596 0.36433 -0.1527 0.0052 1.0000 28.500 0.8952 0.37369 0.37208 -0.1552 0.0050 1.0000 29.000 0.8982 0.38134 0.37975 -0.1576 0.0047 1.0000 29.500 0.9009 0.38889 0.38733 -0.1600 0.0045 1.0000 30.000 0.9033 0.39623 0.39469 -0.1624 0.0043 1.0000 30.500 0.9053 0.40321 0.40169 -0.1646 0.0041 1.0000 31.500 0.9090 0.41961 0.41815 -0.1691 0.0039 1.0000 32.000 0.9100 0.42767 0.42623 -0.1717 0.0039 1.0000 32.500 0.9113 0.43574 0.43431 -0.1742 0.0038 1.0000 33.000 0.9126 0.44369 0.44229 -0.1766 0.0037 1.0000 33.500 0.9136 0.45142 0.45004 -0.1789 0.0035 1.0000 34.000 0.9140 0.45898 0.45763 -0.1812 0.0032 1.0000 34.500 0.9141 0.46639 0.46506 -0.1834 0.0031 1.0000 35.000 0.9139 0.47365 0.47236 -0.1857 0.0029 1.0000 35.500 0.9133 0.48082 0.47955 -0.1880 0.0027 1.0000 36.000 0.9124 0.48777 0.48653 -0.1903 0.0025 1.0000 36.500 0.9112 0.49447 0.49325 -0.1925 0.0024 1.0000 37.000 0.9094 0.50094 0.49976 -0.1948 0.0023 1.0000 37.500 0.9071 0.50743 0.50628 -0.1969 0.0022 1.0000 39.000 0.9010 0.52890 0.52782 -0.2034 0.0021 1.0000 39.500 0.8986 0.53561 0.53455 -0.2055 0.0021 1.0000 40.000 0.8959 0.54198 0.54095 -0.2076 0.0021 1.0000 40.500 0.8929 0.54826 0.54726 -0.2096 0.0020 1.0000 41.000 0.8897 0.55430 0.55332 -0.2117 0.0019 1.0000 41.500 0.8860 0.56011 0.55916 -0.2137 0.0017 1.0000 42.000 0.8820 0.56574 0.56482 -0.2157 0.0015 1.0000 42.500 0.8778 0.57117 0.57028 -0.2177 0.0013 1.0000 43.000 0.8731 0.57621 0.57535 -0.2197 0.0012 1.0000 43.500 0.8680 0.58089 0.58005 -0.2217 0.0011 1.0000 44.000 0.8623 0.58516 0.58435 -0.2237 0.0010 1.0000 45.500 0.8464 0.59991 0.59917 -0.2292 0.0010 1.0000 46.000 0.8409 0.60446 0.60374 -0.2309 0.0009 1.0000 46.500 0.8351 0.60864 0.60795 -0.2326 0.0009 1.0000 47.000 0.8290 0.61264 0.61197 -0.2343 0.0008 1.0000 47.500 0.8226 0.61624 0.61560 -0.2360 0.0007 1.0000 48.000 0.8158 0.61942 0.61880 -0.2377 0.0005 1.0000 48.500 0.8088 0.62234 0.62174 -0.2394 0.0004 1.0000 49.000 0.8015 0.62469 0.62412 -0.2410 0.0004 1.0000 49.500 0.7937 0.62656 0.62601 -0.2428 0.0003 1.0000 51.000 0.7707 0.63332 0.63284 -0.2473 0.0003 1.0000 51.500 0.7631 0.63539 0.63493 -0.2487 0.0002 1.0000 52.000 0.7551 0.63701 0.63657 -0.2501 0.0002 1.0000 52.500 0.7467 0.63811 0.63769 -0.2515 0.0001 1.0000 53.000 0.7381 0.63868 0.63828 -0.2529 0.0001 1.0000 53.500 0.7293 0.63891 0.63854 -0.2542 0.0000 1.0000 54.000 0.7202 0.63855 0.63820 -0.2556 0.0000 1.0000 54.500 0.7107 0.63764 0.63731 -0.2570 0.0000 1.0000