XFOIL Version 6.94 Calculated polar for: E216 (10.4%) 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 ------- -------- --------- --------- -------- ------- ------- 0.000 0.8127 0.00748 0.00283 -0.2020 0.8520 0.6092 0.500 0.8760 0.00745 0.00283 -0.2033 0.8283 0.6602 1.000 0.9317 0.00753 0.00292 -0.2029 0.7995 0.7086 1.500 0.9847 0.00768 0.00308 -0.2019 0.7683 0.7569 2.000 1.0339 0.00790 0.00328 -0.2000 0.7342 0.8046 2.500 1.0782 0.00817 0.00353 -0.1971 0.6964 0.8544 3.000 1.1146 0.00840 0.00372 -0.1925 0.6589 0.9170 3.500 1.1567 0.00874 0.00393 -0.1894 0.6195 1.0000 4.000 1.2041 0.00930 0.00432 -0.1876 0.5751 1.0000 4.500 1.2489 0.00997 0.00480 -0.1854 0.5302 1.0000 5.000 1.2928 0.01067 0.00533 -0.1830 0.4832 1.0000 5.500 1.3338 0.01147 0.00594 -0.1801 0.4353 1.0000 6.000 1.3699 0.01250 0.00670 -0.1763 0.3735 1.0000 6.500 1.4062 0.01361 0.00756 -0.1727 0.3172 1.0000 7.000 1.4415 0.01487 0.00857 -0.1691 0.2573 1.0000 7.500 1.4749 0.01628 0.00972 -0.1653 0.2025 1.0000 8.000 1.5058 0.01788 0.01107 -0.1612 0.1511 1.0000 8.500 1.5355 0.01957 0.01256 -0.1570 0.1080 1.0000 9.000 1.5618 0.02150 0.01431 -0.1524 0.0715 1.0000 9.500 1.5763 0.02437 0.01690 -0.1463 0.0282 1.0000 10.000 1.5927 0.02717 0.01972 -0.1406 0.0176 1.0000 10.500 1.6133 0.02964 0.02239 -0.1359 0.0156 1.0000 11.000 1.6276 0.03272 0.02566 -0.1309 0.0142 1.0000 11.500 1.6287 0.03716 0.03035 -0.1251 0.0133 1.0000 12.000 1.6343 0.04148 0.03492 -0.1206 0.0129 1.0000 12.500 1.6365 0.04651 0.04022 -0.1167 0.0125 1.0000 13.000 1.6359 0.05229 0.04627 -0.1136 0.0121 1.0000 13.500 1.6345 0.05867 0.05290 -0.1115 0.0116 1.0000 14.000 1.6314 0.06572 0.06023 -0.1103 0.0112 1.0000 14.500 1.6262 0.07351 0.06826 -0.1099 0.0108 1.0000 15.000 1.6194 0.08202 0.07703 -0.1104 0.0106 1.0000 15.500 1.6109 0.09113 0.08642 -0.1115 0.0104 1.0000 16.000 1.6010 0.10083 0.09640 -0.1134 0.0102 1.0000 16.500 1.5888 0.11123 0.10714 -0.1164 0.0101 1.0000 17.000 1.5716 0.12288 0.11914 -0.1208 0.0099 1.0000 17.500 1.5536 0.13525 0.13187 -0.1269 0.0099 1.0000 18.000 1.5316 0.14911 0.14610 -0.1351 0.0099 1.0000 18.500 1.5081 0.16406 0.16139 -0.1450 0.0099 1.0000 19.000 1.4856 0.17980 0.17746 -0.1562 0.0100 1.0000 19.500 1.4630 0.19699 0.19496 -0.1689 0.0101 1.0000