XFOIL Version 6.94 Calculated polar for: GOE 550 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 0.5019 0.01132 0.00399 -0.1177 0.6967 0.3013 0.500 0.5542 0.01120 0.00388 -0.1166 0.6773 0.3133 1.000 0.6067 0.01116 0.00382 -0.1156 0.6581 0.3253 1.500 0.6585 0.01107 0.00378 -0.1145 0.6382 0.3392 2.000 0.7101 0.01106 0.00380 -0.1133 0.6187 0.3586 3.500 0.8634 0.01019 0.00423 -0.1094 0.5208 1.0000 4.000 0.9017 0.01071 0.00438 -0.1057 0.4648 1.0000 4.500 0.9451 0.01119 0.00469 -0.1030 0.4284 1.0000 5.000 0.9814 0.01192 0.00511 -0.0992 0.3758 1.0000 5.500 1.0178 0.01271 0.00564 -0.0954 0.3323 1.0000 6.000 1.0577 0.01336 0.00619 -0.0924 0.3039 1.0000 6.500 1.0825 0.01451 0.00695 -0.0868 0.2372 1.0000 7.000 1.0830 0.01682 0.00849 -0.0777 0.1166 1.0000 7.500 1.1002 0.01850 0.00987 -0.0716 0.0625 1.0000 8.000 1.1076 0.02075 0.01181 -0.0646 0.0095 1.0000 8.500 1.1310 0.02227 0.01337 -0.0601 0.0053 1.0000 9.500 1.1783 0.02558 0.01692 -0.0524 0.0047 1.0000 10.000 1.1986 0.02765 0.01915 -0.0488 0.0046 1.0000 10.500 1.2154 0.03014 0.02181 -0.0454 0.0046 1.0000 11.000 1.2298 0.03301 0.02487 -0.0423 0.0046 1.0000 11.500 1.2410 0.03637 0.02842 -0.0396 0.0046 1.0000 12.000 1.2491 0.04028 0.03254 -0.0373 0.0046 1.0000 12.500 1.2545 0.04472 0.03719 -0.0355 0.0047 1.0000 13.000 1.2560 0.04990 0.04258 -0.0344 0.0047 1.0000 13.500 1.2545 0.05583 0.04873 -0.0339 0.0047 1.0000 14.000 1.2492 0.06265 0.05577 -0.0341 0.0048 1.0000 14.500 1.2397 0.07047 0.06381 -0.0352 0.0048 1.0000 15.000 1.2326 0.07839 0.07193 -0.0368 0.0048 1.0000 15.500 1.2273 0.08638 0.08012 -0.0389 0.0049 1.0000 16.000 1.2228 0.09455 0.08847 -0.0412 0.0049 1.0000 16.500 1.2201 0.10269 0.09680 -0.0439 0.0050 1.0000 17.000 1.2178 0.11091 0.10521 -0.0469 0.0051 1.0000 17.500 1.2170 0.11895 0.11344 -0.0499 0.0053 1.0000 18.000 1.2172 0.12684 0.12150 -0.0531 0.0054 1.0000 18.500 1.2194 0.13427 0.12911 -0.0562 0.0055 1.0000 19.000 1.2206 0.14200 0.13704 -0.0596 0.0057 1.0000 19.500 1.2217 0.14977 0.14501 -0.0634 0.0059 1.0000 20.000 1.2210 0.15794 0.15338 -0.0676 0.0061 1.0000 20.500 1.2171 0.16694 0.16260 -0.0728 0.0062 1.0000 21.000 1.2109 0.17651 0.17239 -0.0785 0.0063 1.0000 21.500 1.2030 0.18669 0.18278 -0.0848 0.0065 1.0000 22.000 1.1915 0.19882 0.19517 -0.0930 0.0066 1.0000 22.500 1.1667 0.21569 0.21237 -0.1041 0.0067 1.0000 23.000 0.8749 0.30111 0.29899 -0.1450 0.0198 1.0000 23.500 0.8836 0.30923 0.30713 -0.1481 0.0190 1.0000 24.000 0.8967 0.31588 0.31381 -0.1498 0.0186 1.0000 24.500 0.8953 0.32940 0.32733 -0.1556 0.0173 1.0000 25.000 0.9025 0.33812 0.33607 -0.1588 0.0162 1.0000 25.500 0.9118 0.34551 0.34349 -0.1612 0.0157 1.0000 26.000 0.9147 0.35764 0.35562 -0.1656 0.0150 1.0000 26.500 0.9206 0.36715 0.36516 -0.1689 0.0141 1.0000 27.000 0.9269 0.37583 0.37386 -0.1720 0.0133 1.0000 27.500 0.9341 0.38363 0.38169 -0.1745 0.0130 1.0000 28.000 0.9372 0.39538 0.39346 -0.1784 0.0126 1.0000 28.500 0.9418 0.40553 0.40362 -0.1817 0.0118 1.0000 29.000 0.9466 0.41475 0.41287 -0.1848 0.0111 1.0000 29.500 0.9512 0.42349 0.42164 -0.1877 0.0108 1.0000 30.000 0.9560 0.43154 0.42972 -0.1903 0.0105 1.0000 30.500 0.9592 0.44160 0.43980 -0.1934 0.0104 1.0000 31.000 0.9618 0.45221 0.45043 -0.1968 0.0103 1.0000 31.500 0.9647 0.46228 0.46053 -0.1999 0.0100 1.0000 32.000 0.9674 0.47197 0.47024 -0.2028 0.0096 1.0000 32.500 0.9697 0.48119 0.47949 -0.2057 0.0095 1.0000 33.000 0.9717 0.49028 0.48861 -0.2086 0.0092 1.0000 33.500 0.9735 0.49929 0.49765 -0.2114 0.0090 1.0000 34.000 0.9747 0.50799 0.50638 -0.2141 0.0088 1.0000 34.500 0.9757 0.51670 0.51512 -0.2169 0.0088 1.0000 35.000 0.9764 0.52511 0.52356 -0.2196 0.0085 1.0000 35.500 0.9768 0.53338 0.53187 -0.2222 0.0085 1.0000 36.000 0.9769 0.54140 0.53991 -0.2247 0.0084 1.0000 36.500 0.9767 0.54962 0.54817 -0.2272 0.0084 1.0000 38.500 0.9711 0.58326 0.58193 -0.2377 0.0083 1.0000 39.000 0.9690 0.59121 0.58992 -0.2403 0.0083 1.0000 39.500 0.9667 0.59965 0.59839 -0.2427 0.0082 1.0000 40.000 0.9643 0.60782 0.60659 -0.2451 0.0081 1.0000 40.500 0.9615 0.61581 0.61462 -0.2474 0.0077 1.0000 41.000 0.9583 0.62321 0.62205 -0.2497 0.0073 1.0000 41.500 0.9548 0.63035 0.62922 -0.2520 0.0069 1.0000 42.000 0.9508 0.63666 0.63557 -0.2542 0.0067 1.0000 42.500 0.9465 0.64252 0.64146 -0.2563 0.0065 1.0000 43.000 0.9420 0.65062 0.64958 -0.2584 0.0064 1.0000 43.500 0.9378 0.65879 0.65778 -0.2605 0.0063 1.0000 44.000 0.9331 0.66591 0.66494 -0.2624 0.0058 1.0000 44.500 0.9280 0.67209 0.67115 -0.2644 0.0055 1.0000 45.000 0.9225 0.67766 0.67674 -0.2663 0.0052 1.0000 45.500 0.9165 0.68210 0.68121 -0.2683 0.0049 1.0000 46.500 0.9042 0.69424 0.69340 -0.2718 0.0047 1.0000 47.000 0.8983 0.70066 0.69985 -0.2735 0.0045 1.0000 47.500 0.8917 0.70553 0.70475 -0.2751 0.0042 1.0000 48.000 0.8848 0.70981 0.70906 -0.2767 0.0038 1.0000 48.500 0.8775 0.71304 0.71232 -0.2784 0.0036 1.0000 49.000 0.8696 0.71538 0.71468 -0.2800 0.0034 1.0000 50.000 0.8543 0.72371 0.72306 -0.2828 0.0033 1.0000 50.500 0.8468 0.72793 0.72730 -0.2841 0.0032 1.0000 51.000 0.8388 0.73076 0.73016 -0.2854 0.0030 1.0000 51.500 0.8304 0.73297 0.73240 -0.2867 0.0027 1.0000 52.000 0.8218 0.73438 0.73384 -0.2879 0.0025 1.0000 52.500 0.8128 0.73503 0.73450 -0.2892 0.0023 1.0000 53.000 0.8034 0.73489 0.73439 -0.2904 0.0021 1.0000 54.500 0.7754 0.73694 0.73650 -0.2935 0.0020 1.0000 55.000 0.7661 0.73731 0.73690 -0.2943 0.0020 1.0000 55.500 0.7565 0.73702 0.73662 -0.2952 0.0019 1.0000 56.000 0.7467 0.73594 0.73557 -0.2960 0.0019 1.0000 56.500 0.7367 0.73446 0.73411 -0.2967 0.0017 1.0000 57.000 0.7265 0.73228 0.73194 -0.2975 0.0015 1.0000 57.500 0.7161 0.72958 0.72927 -0.2982 0.0013 1.0000 58.000 0.7055 0.72616 0.72587 -0.2988 0.0012 1.0000 58.500 0.6947 0.72240 0.72213 -0.2995 0.0011 1.0000 59.000 0.6838 0.71799 0.71774 -0.3001 0.0010 1.0000 59.500 0.6722 0.71250 0.71226 -0.3007 0.0010 1.0000