XFOIL Version 6.94 Calculated polar for: MH 82 13.31% 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 0.2755 0.00993 0.00423 -0.0176 0.4018 0.9786 0.500 0.3728 0.00995 0.00403 -0.0255 0.3888 1.0000 1.000 0.4231 0.01016 0.00397 -0.0243 0.3762 1.0000 1.500 0.4729 0.01078 0.00433 -0.0232 0.3582 1.0000 2.000 0.5239 0.01099 0.00447 -0.0221 0.3529 1.0000 2.500 0.5755 0.01125 0.00466 -0.0211 0.3458 1.0000 3.000 0.6272 0.01156 0.00488 -0.0202 0.3374 1.0000 3.500 0.6789 0.01195 0.00510 -0.0193 0.3272 1.0000 4.000 0.7296 0.01308 0.00613 -0.0186 0.3118 1.0000 4.500 0.7832 0.01339 0.00645 -0.0181 0.3093 1.0000 5.000 0.8369 0.01380 0.00689 -0.0177 0.3050 1.0000 5.500 0.8905 0.01429 0.00741 -0.0174 0.2997 1.0000 6.000 0.9439 0.01480 0.00795 -0.0171 0.2937 1.0000 6.500 0.9970 0.01531 0.00845 -0.0168 0.2872 1.0000 7.000 1.0490 0.01602 0.00910 -0.0164 0.2782 1.0000 7.500 1.0974 0.01784 0.01106 -0.0161 0.2687 1.0000 8.000 1.1496 0.01835 0.01169 -0.0159 0.2663 1.0000 8.500 1.2006 0.01903 0.01253 -0.0156 0.2626 1.0000 9.000 1.2503 0.01982 0.01346 -0.0152 0.2578 1.0000 9.500 1.2996 0.02055 0.01428 -0.0148 0.2521 1.0000 10.000 1.3486 0.02108 0.01485 -0.0143 0.2459 1.0000 10.500 1.3946 0.02201 0.01582 -0.0137 0.2392 1.0000 11.000 1.4273 0.02530 0.01942 -0.0125 0.2292 1.0000 11.500 1.4711 0.02582 0.02011 -0.0117 0.2269 1.0000 12.000 1.5088 0.02665 0.02114 -0.0105 0.2227 1.0000 12.500 1.5396 0.02796 0.02265 -0.0088 0.2175 1.0000 13.000 1.5623 0.02925 0.02406 -0.0065 0.2116 1.0000 13.500 1.5837 0.03087 0.02574 -0.0051 0.2055 1.0000 14.000 1.5954 0.03394 0.02888 -0.0040 0.1978 1.0000 14.500 1.5846 0.03962 0.03485 -0.0037 0.1916 1.0000 15.000 1.5725 0.04559 0.04110 -0.0054 0.1881 1.0000 15.500 1.5447 0.05397 0.04974 -0.0083 0.1826 1.0000 16.000 1.5195 0.06284 0.05881 -0.0118 0.1758 1.0000 16.500 1.5155 0.06935 0.06546 -0.0144 0.1687 1.0000 18.500 1.0960 0.17083 0.16740 -0.0669 0.1111 1.0000 19.000 1.1314 0.17072 0.16737 -0.0672 0.1079 1.0000 19.500 1.1783 0.16801 0.16477 -0.0663 0.1060 1.0000 20.500 1.1110 0.20336 0.20023 -0.0849 0.0843 1.0000 21.000 1.1554 0.19978 0.19675 -0.0841 0.0821 1.0000 22.000 1.1066 0.23605 0.23312 -0.1008 0.0644 1.0000 22.500 1.1303 0.23828 0.23553 -0.1027 0.0607 1.0000 23.000 1.1768 0.23257 0.22993 -0.1019 0.0590 1.0000 23.500 1.1178 0.26516 0.26252 -0.1142 0.0474 1.0000 24.000 1.1287 0.27201 0.26945 -0.1177 0.0427 1.0000 24.500 1.1608 0.27008 0.26763 -0.1188 0.0406 1.0000 25.500 1.0730 0.32649 0.32409 -0.1338 0.0274 1.0000 26.000 1.0910 0.32733 0.32502 -0.1359 0.0248 1.0000 26.500 0.9185 0.32442 0.32232 -0.1270 0.0213 1.0000 27.000 0.8853 0.32963 0.32760 -0.1282 0.0192 1.0000 27.500 0.8658 0.33413 0.33215 -0.1294 0.0192 1.0000 29.000 0.8371 0.34721 0.34535 -0.1347 0.0173 1.0000 29.500 0.8395 0.34845 0.34664 -0.1367 0.0139 1.0000 30.000 0.8353 0.35204 0.35027 -0.1385 0.0136 1.0000 31.500 0.8195 0.36307 0.36137 -0.1432 0.0116 1.0000 32.000 0.8174 0.36702 0.36535 -0.1454 0.0115 1.0000 32.500 0.8154 0.37117 0.36954 -0.1476 0.0115 1.0000 33.000 0.8136 0.37454 0.37294 -0.1498 0.0115 1.0000 33.500 0.8121 0.37974 0.37816 -0.1525 0.0110 1.0000 34.000 0.8123 0.38544 0.38389 -0.1554 0.0089 1.0000 34.500 0.8109 0.38892 0.38743 -0.1572 0.0065 1.0000 35.000 0.8104 0.39216 0.39070 -0.1597 0.0058 1.0000