XFOIL Version 6.94 Calculated polar for: MRC-20 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 0.3879 0.00790 0.00291 -0.0794 0.7715 0.7327 0.500 0.4403 0.00784 0.00284 -0.0787 0.7523 0.7573 1.000 0.4913 0.00783 0.00283 -0.0777 0.7316 0.7869 1.500 0.5411 0.00785 0.00288 -0.0764 0.7097 0.8223 2.000 0.5900 0.00793 0.00299 -0.0749 0.6868 0.8623 2.500 0.6393 0.00809 0.00316 -0.0734 0.6631 0.9032 3.000 0.6932 0.00839 0.00340 -0.0730 0.6386 0.9402 3.500 0.7589 0.00875 0.00368 -0.0754 0.6122 0.9642 4.000 0.8301 0.00917 0.00399 -0.0793 0.5833 0.9807 4.500 0.9055 0.00963 0.00435 -0.0843 0.5529 0.9926 5.000 0.9682 0.01008 0.00468 -0.0868 0.5217 1.0000 6.000 1.0051 0.01074 0.00519 -0.0723 0.4704 1.0000 6.500 1.0295 0.01124 0.00557 -0.0664 0.4438 1.0000 7.000 1.0620 0.01181 0.00608 -0.0624 0.4169 1.0000 7.500 1.0963 0.01248 0.00670 -0.0590 0.3893 1.0000 8.000 1.1296 0.01329 0.00742 -0.0556 0.3616 1.0000 8.500 1.1644 0.01411 0.00821 -0.0526 0.3322 1.0000 9.000 1.1956 0.01515 0.00918 -0.0492 0.3009 1.0000 9.500 1.2247 0.01637 0.01029 -0.0457 0.2677 1.0000 10.000 1.2540 0.01767 0.01152 -0.0425 0.2352 1.0000 10.500 1.2794 0.01925 0.01302 -0.0390 0.2025 1.0000 11.000 1.3013 0.02110 0.01477 -0.0353 0.1704 1.0000 11.500 1.3193 0.02330 0.01685 -0.0314 0.1387 1.0000 12.000 1.3371 0.02564 0.01913 -0.0279 0.1115 1.0000 12.500 1.3492 0.02849 0.02191 -0.0242 0.0874 1.0000 13.000 1.3596 0.03168 0.02511 -0.0208 0.0677 1.0000 13.500 1.3660 0.03541 0.02885 -0.0177 0.0532 1.0000 14.000 1.3698 0.03966 0.03319 -0.0150 0.0436 1.0000 14.500 1.3694 0.04460 0.03821 -0.0128 0.0370 1.0000 15.000 1.3673 0.05007 0.04388 -0.0112 0.0334 1.0000 15.500 1.3692 0.05542 0.04944 -0.0104 0.0307 1.0000 16.000 1.3633 0.06186 0.05604 -0.0100 0.0283 1.0000 16.500 1.3449 0.07013 0.06453 -0.0101 0.0262 1.0000 17.000 1.3274 0.07846 0.07310 -0.0106 0.0248 1.0000 17.500 1.3239 0.08540 0.08026 -0.0117 0.0241 1.0000 18.000 1.3179 0.09284 0.08792 -0.0132 0.0230 1.0000 18.500 1.3106 0.10060 0.09588 -0.0152 0.0219 1.0000 19.000 1.3015 0.10874 0.10422 -0.0177 0.0210 1.0000 19.500 1.2919 0.11713 0.11279 -0.0206 0.0201 1.0000 20.000 1.2816 0.12573 0.12156 -0.0239 0.0193 1.0000 20.500 1.2699 0.13438 0.13038 -0.0273 0.0185 1.0000 21.000 1.2502 0.14430 0.14058 -0.0314 0.0176 1.0000 21.500 1.2321 0.15511 0.15167 -0.0371 0.0173 1.0000 22.000 1.2163 0.16632 0.16313 -0.0438 0.0171 1.0000 22.500 1.1951 0.17911 0.17620 -0.0519 0.0169 1.0000 23.000 1.1609 0.19600 0.19340 -0.0628 0.0168 1.0000