XFOIL Version 6.96 Calculated polar for: MH 94 16.03% 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -13.250 -0.5363 0.11014 0.10454 -0.0522 1.0000 0.0692 -13.000 -0.6092 0.09137 0.08563 -0.0627 1.0000 0.0609 -12.750 -0.6231 0.08596 0.08020 -0.0642 1.0000 0.0598 -12.500 -0.6571 0.07906 0.07320 -0.0670 1.0000 0.0587 -12.250 -0.6986 0.07278 0.06674 -0.0687 1.0000 0.0576 -12.000 -0.7502 0.06722 0.06091 -0.0684 1.0000 0.0562 -11.750 -0.8247 0.06382 0.05708 -0.0634 1.0000 0.0548 -11.500 -0.8544 0.06227 0.05534 -0.0581 1.0000 0.0543 -11.250 -0.8630 0.05969 0.05268 -0.0547 1.0000 0.0539 -11.000 -0.8721 0.05717 0.05006 -0.0512 1.0000 0.0535 -10.750 -0.8822 0.05470 0.04743 -0.0474 1.0000 0.0532 -10.500 -0.8917 0.05224 0.04475 -0.0435 1.0000 0.0529 -10.250 -0.8971 0.04983 0.04211 -0.0399 1.0000 0.0525 -10.000 -0.8998 0.04747 0.03949 -0.0364 1.0000 0.0524 -9.750 -0.8984 0.04519 0.03697 -0.0332 1.0000 0.0522 -9.500 -0.8942 0.04303 0.03454 -0.0302 1.0000 0.0523 -9.250 -0.8878 0.04108 0.03232 -0.0274 1.0000 0.0528 -9.000 -0.8804 0.03935 0.03028 -0.0245 1.0000 0.0538 -8.750 -0.8685 0.03758 0.02829 -0.0223 1.0000 0.0549 -8.500 -0.8503 0.03605 0.02684 -0.0211 1.0000 0.0568 -8.250 -0.8343 0.03471 0.02545 -0.0193 1.0000 0.0588 -8.000 -0.8179 0.03336 0.02392 -0.0173 1.0000 0.0606 -7.750 -0.7990 0.03189 0.02245 -0.0158 1.0000 0.0626 -7.500 -0.7827 0.03070 0.02136 -0.0140 1.0000 0.0656 -7.250 -0.7682 0.02969 0.02026 -0.0118 1.0000 0.0697 -7.000 -0.7558 0.02853 0.01931 -0.0097 1.0000 0.0747 -6.750 -0.7445 0.02741 0.01825 -0.0073 1.0000 0.0808 -6.500 -0.7348 0.02626 0.01718 -0.0047 1.0000 0.0897 -6.250 -0.7260 0.02503 0.01611 -0.0021 1.0000 0.1027 -6.000 -0.7185 0.02349 0.01486 0.0004 1.0000 0.1305 -5.750 -0.7178 0.02076 0.01331 0.0031 1.0000 0.2597 -5.500 -0.7081 0.01974 0.01299 0.0054 1.0000 0.3900 -5.250 -0.6924 0.01963 0.01307 0.0074 1.0000 0.4473 -5.000 -0.6756 0.01975 0.01327 0.0093 1.0000 0.4877 -4.750 -0.6582 0.01995 0.01348 0.0111 1.0000 0.5198 -4.500 -0.6408 0.02025 0.01381 0.0131 1.0000 0.5464 -4.250 -0.6235 0.02056 0.01408 0.0149 1.0000 0.5726 -4.000 -0.6069 0.02104 0.01464 0.0173 1.0000 0.5947 -3.750 -0.5884 0.02163 0.01528 0.0194 0.9992 0.6162 -3.500 -0.5480 0.02283 0.01649 0.0176 0.9902 0.6396 -3.250 -0.5075 0.02374 0.01735 0.0156 0.9816 0.6575 -3.000 -0.4697 0.02426 0.01780 0.0137 0.9720 0.6729 -2.750 -0.4348 0.02461 0.01806 0.0123 0.9620 0.6883 -2.500 -0.3989 0.02512 0.01854 0.0111 0.9526 0.7006 -2.250 -0.3600 0.02556 0.01894 0.0093 0.9436 0.7134 -2.000 -0.3298 0.02565 0.01895 0.0087 0.9327 0.7274 -1.750 -0.2948 0.02601 0.01931 0.0079 0.9231 0.7385 -1.500 -0.2574 0.02616 0.01941 0.0063 0.9137 0.7504 -1.250 -0.2281 0.02617 0.01937 0.0060 0.9022 0.7632 -1.000 -0.1822 0.02637 0.01955 0.0036 0.8952 0.7728 -0.750 -0.1570 0.02618 0.01932 0.0038 0.8822 0.7854 -0.500 -0.1268 0.02622 0.01937 0.0041 0.8711 0.7944 -0.250 -0.0833 0.02598 0.01909 0.0017 0.8627 0.8060 0.000 -0.0575 0.02590 0.01901 0.0027 0.8499 0.8158 0.250 -0.0065 0.02547 0.01856 -0.0006 0.8438 0.8261 0.500 0.0176 0.02526 0.01835 0.0007 0.8296 0.8365 0.750 0.0505 0.02491 0.01800 0.0005 0.8182 0.8465 1.000 0.0982 0.02427 0.01736 -0.0018 0.8104 0.8564 1.250 0.1321 0.02381 0.01692 -0.0019 0.7985 0.8658 1.500 0.1904 0.02296 0.01607 -0.0059 0.7921 0.8743 1.750 0.2313 0.02245 0.01557 -0.0072 0.7794 0.8829 2.000 0.3082 0.02153 0.01466 -0.0145 0.7720 0.8881 2.250 0.3474 0.02097 0.01409 -0.0157 0.7557 0.8974 2.500 0.4067 0.02042 0.01353 -0.0204 0.7376 0.9028 2.750 0.4486 0.01988 0.01294 -0.0221 0.7170 0.9122 3.000 0.5002 0.01959 0.01259 -0.0257 0.6882 0.9173 3.250 0.5451 0.01930 0.01215 -0.0282 0.6584 0.9249 3.500 0.5846 0.01917 0.01191 -0.0300 0.6238 0.9322 3.750 0.6191 0.01915 0.01174 -0.0310 0.5882 0.9410 4.000 0.6587 0.01921 0.01162 -0.0332 0.5493 0.9481 4.250 0.6879 0.01935 0.01158 -0.0336 0.5127 0.9579 4.500 0.7269 0.01962 0.01160 -0.0360 0.4725 0.9654 4.750 0.7599 0.01993 0.01171 -0.0375 0.4339 0.9742 5.000 0.7929 0.02034 0.01190 -0.0391 0.3965 0.9834 5.250 0.8286 0.02083 0.01216 -0.0414 0.3590 0.9920 5.500 0.8637 0.02142 0.01249 -0.0438 0.3248 1.0000 5.750 0.8660 0.02182 0.01277 -0.0399 0.3059 1.0000 6.000 0.8679 0.02223 0.01304 -0.0359 0.2891 1.0000 6.250 0.8676 0.02257 0.01333 -0.0315 0.2741 1.0000 6.500 0.8670 0.02293 0.01364 -0.0270 0.2608 1.0000 6.750 0.8675 0.02335 0.01396 -0.0227 0.2496 1.0000 7.000 0.8687 0.02373 0.01424 -0.0185 0.2394 1.0000 7.250 0.8754 0.02426 0.01474 -0.0152 0.2290 1.0000 7.500 0.8937 0.02506 0.01535 -0.0141 0.2189 1.0000 7.750 0.9106 0.02576 0.01609 -0.0126 0.2095 1.0000 8.000 0.9362 0.02679 0.01698 -0.0127 0.2015 1.0000 8.250 0.9560 0.02761 0.01788 -0.0117 0.1941 1.0000 8.500 0.9870 0.02882 0.01885 -0.0128 0.1873 1.0000 8.750 1.0039 0.02972 0.01998 -0.0113 0.1820 1.0000 9.000 1.0269 0.03074 0.02104 -0.0109 0.1770 1.0000 9.250 1.0588 0.03213 0.02225 -0.0122 0.1722 1.0000 9.500 1.0747 0.03332 0.02368 -0.0106 0.1686 1.0000 9.750 1.0919 0.03451 0.02506 -0.0094 0.1649 1.0000 10.000 1.1117 0.03573 0.02636 -0.0086 0.1614 1.0000 10.250 1.1374 0.03718 0.02777 -0.0089 0.1585 1.0000 10.500 1.1577 0.03914 0.02984 -0.0085 0.1559 1.0000 10.750 1.1634 0.04070 0.03173 -0.0058 0.1538 1.0000 11.000 1.1697 0.04240 0.03370 -0.0033 0.1516 1.0000 11.250 1.1775 0.04415 0.03564 -0.0012 0.1494 1.0000 11.500 1.1873 0.04595 0.03761 0.0005 0.1475 1.0000 11.750 1.1975 0.04783 0.03962 0.0021 0.1459 1.0000 12.000 1.2104 0.04981 0.04166 0.0031 0.1442 1.0000 12.250 1.2257 0.05283 0.04473 0.0033 0.1425 1.0000 12.500 1.2054 0.05514 0.04734 0.0084 0.1419 1.0000 12.750 1.1808 0.05793 0.05042 0.0130 0.1415 1.0000 13.000 1.1507 0.06137 0.05414 0.0170 0.1412 1.0000 13.250 1.1140 0.06572 0.05877 0.0199 0.1411 1.0000 13.500 1.0704 0.07147 0.06477 0.0213 0.1414 1.0000 13.750 1.0189 0.07927 0.07280 0.0204 0.1420 1.0000