XFOIL Version 6.94 Calculated polar for: E209 (13.72%) 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 0.2377 0.00848 0.00229 -0.0503 0.5995 0.6261 0.500 0.2926 0.00852 0.00233 -0.0500 0.5866 0.6529 1.000 0.3470 0.00850 0.00239 -0.0496 0.5738 0.6835 2.000 0.4539 0.00846 0.00266 -0.0484 0.5498 0.7735 2.500 0.5048 0.00844 0.00283 -0.0471 0.5382 0.8406 3.000 0.5585 0.00842 0.00307 -0.0461 0.5258 0.9191 3.500 0.6340 0.00860 0.00328 -0.0500 0.5110 0.9698 4.000 0.7153 0.00879 0.00347 -0.0556 0.4947 0.9921 4.500 0.7814 0.00897 0.00365 -0.0581 0.4781 1.0000 5.000 0.8262 0.00918 0.00386 -0.0559 0.4619 1.0000 5.500 0.8719 0.00942 0.00412 -0.0539 0.4439 1.0000 6.000 0.9175 0.00970 0.00439 -0.0519 0.4226 1.0000 6.500 0.9638 0.01003 0.00473 -0.0501 0.3997 1.0000 7.000 1.0089 0.01046 0.00515 -0.0482 0.3685 1.0000 7.500 1.0505 0.01112 0.00568 -0.0457 0.3179 1.0000 8.000 1.0843 0.01231 0.00655 -0.0422 0.2415 1.0000 8.500 1.1134 0.01381 0.00772 -0.0382 0.1748 1.0000 9.000 1.1405 0.01530 0.00897 -0.0339 0.1246 1.0000 9.500 1.1622 0.01677 0.01027 -0.0287 0.0874 1.0000 10.000 1.1782 0.01830 0.01173 -0.0228 0.0629 1.0000 10.500 1.1924 0.02009 0.01348 -0.0173 0.0460 1.0000 11.000 1.2046 0.02219 0.01560 -0.0124 0.0350 1.0000 11.500 1.2144 0.02476 0.01828 -0.0083 0.0281 1.0000 12.000 1.2163 0.02835 0.02198 -0.0048 0.0231 1.0000 12.500 1.2250 0.03190 0.02568 -0.0028 0.0192 1.0000 13.000 1.2203 0.03707 0.03103 -0.0012 0.0162 1.0000 13.500 1.2214 0.04208 0.03620 -0.0005 0.0142 1.0000 14.000 1.2093 0.04874 0.04302 -0.0004 0.0129 1.0000 14.500 1.2033 0.05512 0.04961 -0.0007 0.0120 1.0000 15.000 1.2018 0.06141 0.05611 -0.0017 0.0112 1.0000 15.500 1.2018 0.06786 0.06272 -0.0033 0.0104 1.0000 16.000 1.1936 0.07574 0.07076 -0.0055 0.0096 1.0000 16.500 1.1815 0.08433 0.07956 -0.0080 0.0092 1.0000 17.000 1.1717 0.09312 0.08859 -0.0110 0.0089 1.0000 17.500 1.1637 0.10217 0.09791 -0.0148 0.0086 1.0000 18.000 1.1527 0.11227 0.10827 -0.0195 0.0083 1.0000 18.500 1.1379 0.12332 0.11960 -0.0250 0.0082 1.0000 19.000 1.1195 0.13567 0.13224 -0.0317 0.0082 1.0000 19.500 1.0996 0.14901 0.14586 -0.0395 0.0080 1.0000 20.000 1.0718 0.16488 0.16202 -0.0492 0.0081 1.0000 20.500 1.0327 0.18524 0.18270 -0.0616 0.0083 1.0000 22.500 0.7327 0.25889 0.25708 -0.0998 0.0143 1.0000 23.000 0.7424 0.26635 0.26457 -0.1032 0.0136 1.0000 23.500 0.7547 0.27267 0.27091 -0.1059 0.0129 1.0000