XFOIL Version 6.94 Calculated polar for: GOE 426 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 0.4845 0.01042 0.00390 -0.0988 0.5814 0.6351 0.500 0.5324 0.01021 0.00405 -0.0965 0.5715 0.7843 1.000 0.6029 0.01002 0.00412 -0.0987 0.5617 0.9714 1.500 0.6644 0.01024 0.00418 -0.1002 0.5519 1.0000 2.000 0.7189 0.01066 0.00436 -0.1000 0.5424 1.0000 2.500 0.7719 0.01090 0.00459 -0.0996 0.5335 1.0000 3.000 0.8259 0.01121 0.00481 -0.0993 0.5245 1.0000 3.500 0.8799 0.01165 0.00516 -0.0991 0.5153 1.0000 4.000 0.9272 0.01155 0.00493 -0.0973 0.4886 1.0000 4.500 0.9751 0.01161 0.00490 -0.0958 0.4639 1.0000 5.000 1.0247 0.01187 0.00510 -0.0946 0.4464 1.0000 5.500 1.0711 0.01213 0.00528 -0.0930 0.4165 1.0000 6.000 1.1174 0.01255 0.00564 -0.0914 0.3926 1.0000 6.500 1.1555 0.01327 0.00613 -0.0885 0.3488 1.0000 7.000 1.1915 0.01414 0.00684 -0.0853 0.3099 1.0000 7.500 1.2072 0.01576 0.00803 -0.0791 0.2346 1.0000 8.000 1.1771 0.01926 0.01074 -0.0667 0.1064 1.0000 8.500 1.1569 0.02302 0.01409 -0.0579 0.0255 1.0000 9.000 1.1640 0.02581 0.01689 -0.0534 0.0060 1.0000 9.500 1.1812 0.02829 0.01950 -0.0504 0.0056 1.0000 10.000 1.1957 0.03122 0.02261 -0.0479 0.0054 1.0000 10.500 1.2073 0.03469 0.02625 -0.0458 0.0053 1.0000 11.000 1.2166 0.03859 0.03034 -0.0441 0.0053 1.0000 11.500 1.2223 0.04310 0.03504 -0.0427 0.0052 1.0000 12.000 1.2264 0.04807 0.04021 -0.0418 0.0052 1.0000 12.500 1.2292 0.05348 0.04582 -0.0414 0.0053 1.0000 13.000 1.2300 0.05942 0.05195 -0.0414 0.0053 1.0000 13.500 1.2308 0.06562 0.05835 -0.0418 0.0053 1.0000 14.000 1.2303 0.07229 0.06520 -0.0426 0.0054 1.0000 14.500 1.2283 0.07943 0.07254 -0.0438 0.0055 1.0000 15.000 1.2262 0.08685 0.08014 -0.0454 0.0055 1.0000 15.500 1.2247 0.09440 0.08787 -0.0473 0.0056 1.0000 16.000 1.2244 0.10193 0.09557 -0.0493 0.0057 1.0000 16.500 1.2260 0.10919 0.10297 -0.0514 0.0059 1.0000 17.000 1.2315 0.11577 0.10969 -0.0533 0.0060 1.0000 17.500 1.2404 0.12169 0.11573 -0.0550 0.0062 1.0000 18.000 1.2528 0.12684 0.12101 -0.0563 0.0064 1.0000 18.500 1.2684 0.13123 0.12551 -0.0572 0.0066 1.0000 19.000 1.2964 0.13283 0.12715 -0.0560 0.0068 1.0000 19.500 1.2965 0.14099 0.13559 -0.0603 0.0070 1.0000 20.000 1.2930 0.14999 0.14502 -0.0650 0.0073 1.0000 20.500 1.2806 0.16076 0.15628 -0.0708 0.0079 1.0000 21.000 1.2686 0.17151 0.16738 -0.0772 0.0082 1.0000 21.500 1.2553 0.18275 0.17889 -0.0842 0.0085 1.0000 22.000 1.2503 0.19211 0.18844 -0.0901 0.0088 1.0000 22.500 1.2134 0.21181 0.20859 -0.1035 0.0091 1.0000 24.000 0.9033 0.31632 0.31426 -0.1496 0.0204 1.0000 24.500 0.9114 0.32428 0.32225 -0.1526 0.0194 1.0000 25.000 0.9211 0.33233 0.33032 -0.1550 0.0190 1.0000 25.500 0.9205 0.34574 0.34374 -0.1604 0.0173 1.0000 26.000 0.9271 0.35434 0.35237 -0.1636 0.0165 1.0000 26.500 0.9372 0.36131 0.35938 -0.1656 0.0160 1.0000 27.000 0.9368 0.37482 0.37290 -0.1706 0.0154 1.0000 27.500 0.9416 0.38478 0.38289 -0.1741 0.0144 1.0000 28.000 0.9466 0.39389 0.39203 -0.1772 0.0139 1.0000 29.000 0.9565 0.41214 0.41034 -0.1832 0.0132 1.0000 29.500 0.9588 0.42378 0.42200 -0.1870 0.0129 1.0000 30.000 0.9623 0.43418 0.43243 -0.1903 0.0122 1.0000 30.500 0.9657 0.44375 0.44203 -0.1934 0.0119 1.0000 31.000 0.9687 0.45316 0.45148 -0.1965 0.0115 1.0000 31.500 0.9717 0.46215 0.46050 -0.1995 0.0112 1.0000 32.000 0.9745 0.47093 0.46932 -0.2022 0.0110 1.0000 32.500 0.9771 0.48026 0.47868 -0.2049 0.0109 1.0000 33.000 0.9778 0.49098 0.48942 -0.2083 0.0108 1.0000 33.500 0.9789 0.50082 0.49931 -0.2114 0.0108 1.0000 34.000 0.9798 0.51071 0.50923 -0.2144 0.0107 1.0000 34.500 0.9805 0.52062 0.51918 -0.2174 0.0106 1.0000 35.000 0.9809 0.53033 0.52893 -0.2202 0.0104 1.0000 35.500 0.9811 0.53982 0.53845 -0.2231 0.0102 1.0000 36.000 0.9808 0.54911 0.54777 -0.2258 0.0099 1.0000 36.500 0.9802 0.55825 0.55695 -0.2285 0.0094 1.0000 37.000 0.9794 0.56696 0.56570 -0.2312 0.0091 1.0000 37.500 0.9782 0.57447 0.57325 -0.2336 0.0088 1.0000 38.000 0.9764 0.58551 0.58432 -0.2363 0.0086 1.0000 38.500 0.9750 0.59642 0.59526 -0.2389 0.0081 1.0000 39.000 0.9730 0.60587 0.60475 -0.2415 0.0076 1.0000 39.500 0.9705 0.61421 0.61312 -0.2439 0.0071 1.0000 40.000 0.9675 0.62136 0.62030 -0.2462 0.0068 1.0000 40.500 0.9646 0.63276 0.63173 -0.2486 0.0067 1.0000 41.000 0.9619 0.64295 0.64195 -0.2509 0.0061 1.0000 41.500 0.9584 0.65124 0.65027 -0.2532 0.0056 1.0000 42.000 0.9542 0.65835 0.65742 -0.2555 0.0052 1.0000 43.000 0.9462 0.67734 0.67646 -0.2597 0.0049 1.0000 43.500 0.9418 0.68588 0.68502 -0.2617 0.0045 1.0000 44.000 0.9368 0.69324 0.69242 -0.2637 0.0040 1.0000 44.500 0.9313 0.69953 0.69874 -0.2658 0.0037 1.0000 45.500 0.9203 0.71547 0.71473 -0.2696 0.0035 1.0000 46.000 0.9149 0.72328 0.72256 -0.2713 0.0033 1.0000 46.500 0.9089 0.73029 0.72959 -0.2731 0.0029 1.0000 47.000 0.9024 0.73600 0.73533 -0.2749 0.0026 1.0000 47.500 0.8953 0.74057 0.73993 -0.2766 0.0024 1.0000 48.000 0.8876 0.74451 0.74390 -0.2784 0.0023 1.0000 49.000 0.8737 0.75723 0.75666 -0.2814 0.0022 1.0000 49.500 0.8666 0.76290 0.76234 -0.2828 0.0021 1.0000 50.000 0.8591 0.76776 0.76723 -0.2842 0.0020 1.0000 50.500 0.8512 0.77162 0.77112 -0.2855 0.0017 1.0000 51.000 0.8429 0.77482 0.77434 -0.2869 0.0015 1.0000 51.500 0.8343 0.77715 0.77670 -0.2882 0.0013 1.0000 52.000 0.8253 0.77897 0.77854 -0.2895 0.0012 1.0000 52.500 0.8159 0.77981 0.77941 -0.2908 0.0011 1.0000 53.500 0.7981 0.78513 0.78476 -0.2930 0.0010 1.0000 54.000 0.7892 0.78690 0.78655 -0.2939 0.0009 1.0000 54.500 0.7797 0.78732 0.78699 -0.2949 0.0008 1.0000 55.000 0.7698 0.78691 0.78661 -0.2959 0.0007 1.0000 55.500 0.7597 0.78592 0.78564 -0.2968 0.0006 1.0000 57.000 0.7293 0.78313 0.78290 -0.2990 0.0005 1.0000 57.500 0.7188 0.78102 0.78081 -0.2998 0.0004 1.0000 58.000 0.7082 0.77865 0.77845 -0.3004 0.0003 1.0000 58.500 0.6973 0.77515 0.77496 -0.3010 0.0001 1.0000 59.000 0.6863 0.77124 0.77108 -0.3016 0.0000 1.0000