XFOIL Version 6.94 Calculated polar for: MH 116 9.84% 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 0.5154 0.00817 0.00338 -0.1181 0.7869 1.0000 0.500 0.5684 0.00823 0.00333 -0.1175 0.7723 1.0000 1.000 0.6241 0.00832 0.00326 -0.1173 0.7563 1.0000 1.500 0.6793 0.00854 0.00338 -0.1171 0.7400 1.0000 2.000 0.7328 0.00862 0.00343 -0.1165 0.7227 1.0000 2.500 0.7890 0.00887 0.00354 -0.1164 0.7025 1.0000 3.000 0.8413 0.00897 0.00371 -0.1156 0.6852 1.0000 3.500 0.8950 0.00915 0.00380 -0.1149 0.6616 1.0000 4.000 0.9472 0.00934 0.00408 -0.1140 0.6383 1.0000 4.500 0.9990 0.00965 0.00429 -0.1130 0.6071 1.0000 5.000 1.0487 0.00990 0.00463 -0.1116 0.5737 1.0000 5.500 1.0967 0.01032 0.00501 -0.1100 0.5304 1.0000 6.000 1.1401 0.01101 0.00550 -0.1076 0.4705 1.0000 6.500 1.1786 0.01203 0.00624 -0.1045 0.3916 1.0000 7.000 1.2130 0.01337 0.00725 -0.1010 0.3127 1.0000 7.500 1.2424 0.01505 0.00853 -0.0969 0.2287 1.0000 8.000 1.2687 0.01690 0.00999 -0.0925 0.1563 1.0000 8.500 1.2938 0.01858 0.01149 -0.0879 0.1117 1.0000 9.000 1.3135 0.02064 0.01356 -0.0826 0.0726 1.0000 9.500 1.3251 0.02337 0.01605 -0.0769 0.0332 1.0000 11.000 1.3404 0.03451 0.02786 -0.0610 0.0102 1.0000 11.500 1.3332 0.04024 0.03394 -0.0563 0.0085 1.0000 12.000 1.3304 0.04654 0.04067 -0.0525 0.0080 1.0000 12.500 1.3178 0.05496 0.04968 -0.0492 0.0075 1.0000 13.000 1.3005 0.06333 0.05855 -0.0477 0.0074 1.0000 13.500 1.2739 0.07346 0.06917 -0.0482 0.0074 1.0000 14.000 1.2449 0.08479 0.08094 -0.0513 0.0074 1.0000 14.500 1.2183 0.09681 0.09333 -0.0565 0.0074 1.0000 15.000 1.1914 0.11017 0.10703 -0.0640 0.0075 1.0000 15.500 1.1657 0.12468 0.12184 -0.0733 0.0076 1.0000 16.000 1.1426 0.13982 0.13723 -0.0838 0.0078 1.0000 16.500 1.1194 0.15747 0.15508 -0.0952 0.0080 1.0000 17.000 1.0630 0.19392 0.19164 -0.1126 0.0099 1.0000 17.500 1.0435 0.21838 0.21600 -0.1223 0.0120 1.0000 18.000 1.0418 0.23435 0.23193 -0.1282 0.0137 1.0000