XFOIL Version 6.94 Calculated polar for: AH 79-100 C 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 0.8493 0.00997 0.00517 -0.2069 0.8177 0.8407 1.000 0.9656 0.00998 0.00494 -0.2076 0.7952 1.0000 1.500 1.0233 0.01016 0.00498 -0.2080 0.7831 1.0000 2.000 1.0810 0.01029 0.00502 -0.2083 0.7707 1.0000 2.500 1.1304 0.01052 0.00520 -0.2069 0.7563 1.0000 3.000 1.1881 0.01071 0.00533 -0.2073 0.7432 1.0000 3.500 1.2377 0.01089 0.00548 -0.2059 0.7271 1.0000 4.000 1.2814 0.01113 0.00576 -0.2033 0.7097 1.0000 4.500 1.3252 0.01135 0.00599 -0.2007 0.6899 1.0000 5.000 1.3675 0.01162 0.00630 -0.1978 0.6698 1.0000 5.500 1.4060 0.01192 0.00664 -0.1941 0.6477 1.0000 6.000 1.4370 0.01228 0.00697 -0.1888 0.6196 1.0000 6.500 1.4554 0.01282 0.00746 -0.1810 0.5786 1.0000 7.000 1.4712 0.01371 0.00816 -0.1730 0.5260 1.0000 7.500 1.4792 0.01512 0.00927 -0.1640 0.4622 1.0000 8.000 1.4852 0.01693 0.01078 -0.1554 0.3982 1.0000 8.500 1.4912 0.01905 0.01263 -0.1474 0.3354 1.0000 9.000 1.4997 0.02137 0.01474 -0.1404 0.2761 1.0000 9.500 1.5007 0.02448 0.01748 -0.1331 0.2048 1.0000 10.000 1.4837 0.02942 0.02167 -0.1246 0.0955 1.0000 10.500 1.4677 0.03508 0.02681 -0.1173 0.0277 1.0000 11.000 1.4780 0.03883 0.03070 -0.1132 0.0223 1.0000 11.500 1.4833 0.04327 0.03533 -0.1093 0.0204 1.0000 12.000 1.4900 0.04785 0.04014 -0.1060 0.0192 1.0000 12.500 1.4921 0.05321 0.04570 -0.1032 0.0183 1.0000 13.000 1.4898 0.05947 0.05210 -0.1008 0.0176 1.0000 13.500 1.4927 0.06549 0.05830 -0.0990 0.0171 1.0000 14.000 1.5029 0.07090 0.06392 -0.0976 0.0167 1.0000 14.500 1.5186 0.07585 0.06908 -0.0964 0.0163 1.0000 15.000 1.5402 0.08037 0.07383 -0.0952 0.0161 1.0000 15.500 1.5641 0.08502 0.07880 -0.0942 0.0161 1.0000 16.000 1.5774 0.09102 0.08518 -0.0938 0.0159 1.0000 16.500 1.5804 0.09810 0.09264 -0.0941 0.0155 1.0000 17.000 1.5732 0.10681 0.10184 -0.0954 0.0155 1.0000 17.500 1.5534 0.11755 0.11312 -0.0982 0.0159 1.0000 18.000 1.5279 0.12948 0.12554 -0.1029 0.0162 1.0000 18.500 1.5003 0.14224 0.13873 -0.1093 0.0165 1.0000 19.000 1.4721 0.15576 0.15260 -0.1173 0.0168 1.0000 19.500 1.4509 0.16847 0.16556 -0.1253 0.0172 1.0000 21.000 1.0507 0.30713 0.30550 -0.1904 0.0287 1.0000 22.000 1.0595 0.32746 0.32588 -0.1968 0.0242 1.0000 22.500 1.0598 0.34086 0.33928 -0.2011 0.0220 1.0000 23.500 1.0672 0.36293 0.36139 -0.2076 0.0181 1.0000 24.000 1.0746 0.37150 0.36999 -0.2092 0.0173 1.0000 24.500 1.0764 0.38330 0.38181 -0.2129 0.0146 1.0000 25.000 1.0766 0.39852 0.39702 -0.2173 0.0130 1.0000 25.500 1.0809 0.40806 0.40661 -0.2197 0.0121 1.0000 26.000 1.0826 0.42247 0.42101 -0.2233 0.0108 1.0000 26.500 1.0858 0.43327 0.43184 -0.2260 0.0099 1.0000 27.000 1.0896 0.44309 0.44169 -0.2280 0.0095 1.0000 27.500 1.0905 0.45829 0.45689 -0.2318 0.0088 1.0000 28.000 1.0927 0.47010 0.46874 -0.2346 0.0080 1.0000 28.500 1.0946 0.48086 0.47952 -0.2371 0.0076 1.0000 29.000 1.0970 0.49053 0.48923 -0.2391 0.0074 1.0000 29.500 1.0974 0.50467 0.50338 -0.2423 0.0072 1.0000 30.000 1.0986 0.51737 0.51610 -0.2451 0.0070 1.0000 30.500 1.0995 0.52942 0.52818 -0.2477 0.0066 1.0000 31.000 1.1000 0.54115 0.53994 -0.2501 0.0061 1.0000 31.500 1.1002 0.55248 0.55129 -0.2526 0.0058 1.0000 32.000 1.0998 0.56308 0.56193 -0.2549 0.0056 1.0000 32.500 1.0994 0.57327 0.57216 -0.2567 0.0054 1.0000 33.000 1.0983 0.58644 0.58534 -0.2595 0.0053 1.0000 33.500 1.0978 0.59901 0.59794 -0.2619 0.0051 1.0000 34.000 1.0968 0.61076 0.60971 -0.2642 0.0046 1.0000 34.500 1.0951 0.62190 0.62088 -0.2664 0.0043 1.0000 35.000 1.0931 0.63286 0.63188 -0.2685 0.0039 1.0000 35.500 1.0906 0.64308 0.64212 -0.2706 0.0038 1.0000 37.000 1.0817 0.67618 0.67530 -0.2767 0.0035 1.0000 37.500 1.0786 0.68715 0.68629 -0.2787 0.0034 1.0000 38.000 1.0752 0.69766 0.69684 -0.2806 0.0033 1.0000 38.500 1.0712 0.70744 0.70664 -0.2824 0.0031 1.0000 39.000 1.0669 0.71728 0.71651 -0.2843 0.0029 1.0000 39.500 1.0623 0.72679 0.72605 -0.2860 0.0027 1.0000 40.000 1.0572 0.73559 0.73488 -0.2878 0.0026 1.0000 40.500 1.0519 0.74438 0.74370 -0.2895 0.0025 1.0000 41.000 1.0462 0.75245 0.75180 -0.2912 0.0024 1.0000 41.500 1.0402 0.76042 0.75980 -0.2928 0.0023 1.0000 42.000 1.0338 0.76782 0.76723 -0.2944 0.0022 1.0000 42.500 1.0272 0.77526 0.77470 -0.2960 0.0021 1.0000 43.000 1.0197 0.78178 0.78125 -0.2974 0.0020 1.0000 44.500 0.9989 0.80375 0.80329 -0.3016 0.0019 1.0000 45.000 0.9915 0.80993 0.80950 -0.3029 0.0019 1.0000 45.500 0.9839 0.81582 0.81541 -0.3041 0.0018 1.0000 46.000 0.9761 0.82162 0.82123 -0.3053 0.0018 1.0000 46.500 0.9679 0.82671 0.82635 -0.3064 0.0016 1.0000 47.000 0.9594 0.83110 0.83077 -0.3075 0.0015 1.0000 47.500 0.9506 0.83519 0.83488 -0.3086 0.0013 1.0000 48.000 0.9415 0.83866 0.83837 -0.3096 0.0012 1.0000 48.500 0.9322 0.84178 0.84152 -0.3106 0.0010 1.0000 49.000 0.9226 0.84415 0.84391 -0.3116 0.0009 1.0000 49.500 0.9121 0.84573 0.84552 -0.3126 0.0008 1.0000 51.500 0.8729 0.85383 0.85369 -0.3155 0.0008 1.0000 52.000 0.8628 0.85445 0.85433 -0.3161 0.0007 1.0000 52.500 0.8524 0.85476 0.85466 -0.3166 0.0007 1.0000 53.000 0.8417 0.85419 0.85411 -0.3172 0.0006 1.0000 53.500 0.8308 0.85311 0.85305 -0.3177 0.0005 1.0000 54.000 0.8197 0.85147 0.85143 -0.3181 0.0004 1.0000 54.500 0.8084 0.84930 0.84928 -0.3186 0.0004 1.0000 55.000 0.7970 0.84683 0.84683 -0.3190 0.0003 1.0000 55.500 0.7854 0.84353 0.84355 -0.3193 0.0003 1.0000 56.000 0.7736 0.83967 0.83971 -0.3196 0.0002 1.0000 56.500 0.7615 0.83540 0.83546 -0.3199 0.0002 1.0000 57.000 0.7488 0.83040 0.83047 -0.3203 0.0002 1.0000 58.500 0.7136 0.81635 0.81646 -0.3203 0.0001 1.0000 59.000 0.7018 0.81109 0.81122 -0.3203 0.0001 1.0000 59.500 0.6896 0.80476 0.80491 -0.3202 0.0001 1.0000 60.000 0.6772 0.79784 0.79800 -0.3201 0.0001 1.0000