XFOIL Version 6.94 Calculated polar for: MH 117 9.8% 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.3352 0.00746 0.00276 -0.0727 0.7592 0.9797 0.500 0.4006 0.00764 0.00268 -0.0746 0.7360 1.0000 1.000 0.4516 0.00770 0.00269 -0.0735 0.7187 1.0000 1.500 0.5039 0.00790 0.00270 -0.0725 0.6955 1.0000 2.000 0.5569 0.00805 0.00283 -0.0718 0.6754 1.0000 2.500 0.6098 0.00824 0.00289 -0.0708 0.6504 1.0000 3.000 0.6632 0.00842 0.00309 -0.0701 0.6275 1.0000 3.500 0.7156 0.00869 0.00323 -0.0691 0.5960 1.0000 4.000 0.7683 0.00888 0.00345 -0.0682 0.5646 1.0000 4.500 0.8196 0.00921 0.00373 -0.0671 0.5220 1.0000 5.000 0.8689 0.00970 0.00404 -0.0656 0.4645 1.0000 5.500 0.9149 0.01050 0.00452 -0.0638 0.3859 1.0000 6.000 0.9593 0.01155 0.00524 -0.0620 0.3100 1.0000 6.500 1.0035 0.01269 0.00610 -0.0602 0.2380 1.0000 7.000 1.0458 0.01400 0.00724 -0.0583 0.1755 1.0000 7.500 1.0874 0.01539 0.00844 -0.0563 0.1267 1.0000 8.000 1.1248 0.01713 0.00998 -0.0538 0.0880 1.0000 8.500 1.1650 0.01851 0.01145 -0.0515 0.0704 1.0000 9.000 1.1961 0.02069 0.01376 -0.0480 0.0564 1.0000 9.500 1.2326 0.02204 0.01517 -0.0455 0.0454 1.0000 10.500 1.2742 0.02650 0.01987 -0.0368 0.0245 1.0000 11.000 1.2871 0.02957 0.02323 -0.0323 0.0200 1.0000 11.500 1.2998 0.03261 0.02659 -0.0288 0.0151 1.0000 12.000 1.2858 0.03896 0.03328 -0.0246 0.0118 1.0000 12.500 1.2590 0.04795 0.04289 -0.0216 0.0108 1.0000 13.000 1.2626 0.05287 0.04809 -0.0215 0.0103 1.0000 13.500 1.2501 0.06056 0.05617 -0.0225 0.0097 1.0000 14.000 1.2226 0.07093 0.06696 -0.0256 0.0096 1.0000 14.500 1.1880 0.08397 0.08043 -0.0315 0.0095 1.0000 15.000 1.1510 0.09952 0.09635 -0.0405 0.0097 1.0000 15.500 1.1015 0.11996 0.11715 -0.0534 0.0101 1.0000 17.500 0.9732 0.20491 0.20231 -0.0988 0.0119 1.0000 18.000 0.9577 0.23060 0.22791 -0.1080 0.0162 1.0000 19.500 0.9729 0.27091 0.26822 -0.1193 0.0222 1.0000 20.000 0.9801 0.28230 0.27962 -0.1234 0.0220 1.0000 20.500 0.9866 0.29239 0.28971 -0.1286 0.0208 1.0000 21.000 0.9925 0.30382 0.30115 -0.1332 0.0175 1.0000 21.500 0.9964 0.31476 0.31213 -0.1366 0.0152 1.0000 22.000 0.9986 0.32444 0.32192 -0.1392 0.0134 1.0000 22.500 0.9969 0.33268 0.33021 -0.1403 0.0121 1.0000