XFOIL Version 6.94 Calculated polar for: NACA M8 AIRFOIL 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 0.5566 0.01490 0.00699 -0.0678 0.4636 0.0647 0.500 0.6130 0.01461 0.00668 -0.0674 0.4491 0.0870 1.000 0.6675 0.01594 0.00839 -0.0664 0.4360 0.1371 1.500 0.7248 0.01595 0.00808 -0.0660 0.4230 0.1786 2.000 0.7791 0.01675 0.00881 -0.0653 0.4110 0.1998 3.000 0.8577 0.00664 -0.00055 -0.0618 0.3882 0.4020 3.500 0.9096 0.00631 -0.00090 -0.0614 0.3784 0.4416 4.000 0.9617 0.00624 -0.00107 -0.0609 0.3680 0.4644 4.500 1.0147 0.00625 -0.00104 -0.0606 0.3572 0.4768 5.000 1.0677 0.00673 -0.00075 -0.0602 0.3457 0.4573 5.500 1.1220 0.00741 -0.00014 -0.0598 0.3332 0.3975 6.000 1.1736 0.00777 0.00011 -0.0593 0.3165 0.3354 6.500 1.2186 0.00791 0.00002 -0.0581 0.2831 0.3089 7.000 1.2571 0.00847 0.00027 -0.0564 0.2349 0.2928 7.500 1.2852 0.00967 0.00118 -0.0535 0.2065 0.2800 8.000 1.3097 0.01041 0.00194 -0.0501 0.1930 0.2753 8.500 1.3164 0.01131 0.00289 -0.0446 0.1795 0.2707 9.000 1.3213 0.01291 0.00452 -0.0405 0.1675 0.2660 9.500 1.3260 0.01537 0.00706 -0.0375 0.1592 0.2628 10.000 1.3201 0.01928 0.01095 -0.0349 0.1368 0.2616 10.500 1.2966 0.02581 0.01740 -0.0328 0.1044 0.2605 11.000 1.2513 0.03668 0.02821 -0.0319 0.0659 0.2600 11.500 1.2114 0.04914 0.04071 -0.0327 0.0341 0.2596 12.000 1.1805 0.06176 0.05343 -0.0346 0.0052 0.2589 12.500 1.1747 0.07075 0.06263 -0.0362 0.0033 0.2579 13.000 1.1699 0.07977 0.07188 -0.0383 0.0031 0.2571 13.500 1.1629 0.08926 0.08161 -0.0409 0.0031 0.2568 14.000 1.1529 0.09918 0.09179 -0.0441 0.0030 0.2566 14.500 1.1393 0.10946 0.10234 -0.0480 0.0030 0.2564 15.000 1.1242 0.11950 0.11266 -0.0524 0.0031 0.2560 15.500 1.1069 0.12928 0.12273 -0.0573 0.0031 0.2556 16.000 1.0822 0.13858 0.13237 -0.0635 0.0031 0.2555 16.500 1.0647 0.14755 0.14164 -0.0692 0.0032 0.2554 17.000 1.0529 0.15600 0.15034 -0.0745 0.0032 0.2553 17.500 1.0466 0.16374 0.15830 -0.0793 0.0033 0.2551 18.000 1.0427 0.17128 0.16604 -0.0840 0.0034 0.2553 18.500 1.0413 0.17848 0.17343 -0.0885 0.0035 0.2556 19.000 1.0400 0.18590 0.18104 -0.0930 0.0036 0.2559 19.500 1.0375 0.19377 0.18908 -0.0978 0.0036 0.2564 20.000 1.0369 0.20143 0.19691 -0.1024 0.0038 0.2571 20.500 1.0377 0.20894 0.20458 -0.1068 0.0039 0.2580 21.000 1.0391 0.21642 0.21220 -0.1111 0.0041 0.2590 21.500 1.0431 0.22323 0.21912 -0.1150 0.0044 0.2601 22.000 1.0579 0.22657 0.22243 -0.1173 0.0047 0.2631 22.500 1.0741 0.22957 0.22546 -0.1194 0.0051 0.2689 23.000 1.0965 0.23044 0.22638 -0.1204 0.0058 0.2754 23.500 1.1226 0.23035 0.22638 -0.1208 0.0068 0.2968 24.500 1.1767 0.22370 0.22046 -0.1156 0.0099 1.0000 25.000 1.1882 0.22795 0.22504 -0.1177 0.0121 1.0000 25.500 1.1544 0.24558 0.24318 -0.1269 0.0128 1.0000 26.000 1.0067 0.33893 0.33660 -0.1591 0.0152 0.2798 26.500 1.0264 0.31807 0.31641 -0.1536 0.0121 1.0000 28.500 0.9980 0.40059 0.39890 -0.1727 0.0205 1.0000 29.000 0.9988 0.41316 0.41147 -0.1764 0.0179 1.0000 29.500 1.0011 0.42443 0.42275 -0.1796 0.0161 1.0000 30.000 1.0054 0.43232 0.43067 -0.1823 0.0145 1.0000 30.500 1.0058 0.44551 0.44387 -0.1859 0.0126 1.0000 31.500 1.0095 0.46657 0.46496 -0.1920 0.0101 1.0000 32.000 1.0124 0.47463 0.47305 -0.1945 0.0097 1.0000 32.500 1.0116 0.48906 0.48750 -0.1981 0.0084 1.0000 33.000 1.0146 0.49524 0.49371 -0.2003 0.0079 1.0000 33.500 1.0126 0.51171 0.51018 -0.2040 0.0072 1.0000 34.000 1.0129 0.52185 0.52036 -0.2069 0.0067 1.0000 34.500 1.0138 0.52882 0.52736 -0.2093 0.0063 1.0000 35.000 1.0125 0.54272 0.54127 -0.2124 0.0061 1.0000 35.500 1.0116 0.55452 0.55310 -0.2153 0.0058 1.0000 36.000 1.0108 0.56502 0.56362 -0.2180 0.0053 1.0000 36.500 1.0095 0.57451 0.57315 -0.2207 0.0051 1.0000 37.000 1.0081 0.58278 0.58146 -0.2233 0.0049 1.0000 37.500 1.0064 0.59214 0.59084 -0.2258 0.0049 1.0000 38.000 1.0037 0.60411 0.60284 -0.2285 0.0048 1.0000 38.500 1.0012 0.61489 0.61364 -0.2312 0.0048 1.0000 39.000 0.9984 0.62530 0.62409 -0.2337 0.0046 1.0000 39.500 0.9952 0.63474 0.63357 -0.2362 0.0045 1.0000 40.000 0.9919 0.64415 0.64301 -0.2386 0.0044 1.0000 40.500 0.9882 0.65317 0.65206 -0.2410 0.0043 1.0000 41.000 0.9841 0.66182 0.66075 -0.2434 0.0042 1.0000 41.500 0.9797 0.67025 0.66922 -0.2457 0.0042 1.0000 42.000 0.9751 0.67846 0.67746 -0.2480 0.0041 1.0000 42.500 0.9702 0.68637 0.68541 -0.2503 0.0040 1.0000 43.000 0.9650 0.69398 0.69306 -0.2525 0.0040 1.0000 43.500 0.9594 0.70124 0.70035 -0.2547 0.0039 1.0000 44.000 0.9536 0.70819 0.70733 -0.2568 0.0039 1.0000 44.500 0.9475 0.71471 0.71389 -0.2589 0.0038 1.0000 45.000 0.9410 0.72026 0.71949 -0.2610 0.0037 1.0000 46.000 0.9274 0.73331 0.73259 -0.2648 0.0037 1.0000 46.500 0.9208 0.74159 0.74090 -0.2667 0.0036 1.0000 47.000 0.9142 0.74927 0.74861 -0.2684 0.0033 1.0000 47.500 0.9068 0.75508 0.75446 -0.2702 0.0031 1.0000 48.000 0.8991 0.76018 0.75958 -0.2719 0.0029 1.0000 48.500 0.8910 0.76406 0.76350 -0.2737 0.0028 1.0000 49.000 0.8823 0.76690 0.76638 -0.2754 0.0027 1.0000 50.000 0.8662 0.77938 0.77889 -0.2783 0.0026 1.0000 50.500 0.8580 0.78426 0.78380 -0.2797 0.0025 1.0000 51.000 0.8493 0.78799 0.78756 -0.2811 0.0022 1.0000 51.500 0.8401 0.79070 0.79029 -0.2824 0.0021 1.0000 52.000 0.8307 0.79289 0.79251 -0.2838 0.0020 1.0000 52.500 0.8208 0.79399 0.79364 -0.2852 0.0019 1.0000 53.000 0.8103 0.79366 0.79335 -0.2866 0.0018 1.0000 54.000 0.7915 0.80010 0.79982 -0.2887 0.0018 1.0000 54.500 0.7820 0.80229 0.80204 -0.2896 0.0017 1.0000 55.000 0.7719 0.80312 0.80289 -0.2906 0.0016 1.0000 55.500 0.7615 0.80304 0.80283 -0.2915 0.0014 1.0000 56.000 0.7509 0.80217 0.80199 -0.2925 0.0013 1.0000 56.500 0.7400 0.80071 0.80055 -0.2934 0.0012 1.0000 57.000 0.7288 0.79846 0.79832 -0.2943 0.0011 1.0000 57.500 0.7173 0.79529 0.79518 -0.2952 0.0011 1.0000 59.500 0.6726 0.78642 0.78638 -0.2977 0.0010 1.0000 60.000 0.6613 0.78307 0.78305 -0.2981 0.0010 1.0000