XFOIL Version 6.94 Calculated polar for: GOE 528 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 0.6366 0.01178 0.00374 -0.1171 0.5941 0.1112 0.500 0.6763 0.01044 0.00404 -0.1145 0.5804 0.6424 2.000 0.8708 0.01086 0.00444 -0.1197 0.5391 1.0000 2.500 0.9192 0.01114 0.00465 -0.1182 0.5265 1.0000 3.000 0.9688 0.01157 0.00493 -0.1169 0.5142 1.0000 3.500 1.0166 0.01187 0.00517 -0.1153 0.5015 1.0000 4.000 1.0649 0.01229 0.00553 -0.1139 0.4890 1.0000 4.500 1.1116 0.01263 0.00582 -0.1121 0.4759 1.0000 5.000 1.1583 0.01304 0.00623 -0.1105 0.4637 1.0000 5.500 1.1902 0.01315 0.00618 -0.1058 0.4305 1.0000 6.000 1.2242 0.01359 0.00648 -0.1017 0.4035 1.0000 6.500 1.2551 0.01410 0.00691 -0.0972 0.3714 1.0000 7.000 1.2837 0.01474 0.00748 -0.0924 0.3489 1.0000 7.500 1.2973 0.01587 0.00834 -0.0853 0.3039 1.0000 8.000 1.3186 0.01702 0.00937 -0.0801 0.2736 1.0000 8.500 1.3297 0.01876 0.01088 -0.0739 0.2311 1.0000 9.000 1.3376 0.02096 0.01286 -0.0682 0.1917 1.0000 9.500 1.3466 0.02341 0.01518 -0.0632 0.1587 1.0000 10.000 1.3240 0.02833 0.01967 -0.0565 0.0825 1.0000 10.500 1.3107 0.03331 0.02448 -0.0520 0.0407 1.0000 11.000 1.2923 0.03939 0.03043 -0.0484 0.0035 1.0000 11.500 1.3023 0.04330 0.03451 -0.0468 0.0029 1.0000 12.000 1.3104 0.04766 0.03905 -0.0456 0.0028 1.0000 12.500 1.3162 0.05252 0.04411 -0.0447 0.0027 1.0000 13.000 1.3191 0.05795 0.04975 -0.0443 0.0027 1.0000 13.500 1.3191 0.06400 0.05601 -0.0442 0.0027 1.0000 14.000 1.3179 0.07038 0.06261 -0.0446 0.0027 1.0000 14.500 1.3142 0.07733 0.06980 -0.0452 0.0027 1.0000 15.000 1.3100 0.08457 0.07726 -0.0463 0.0027 1.0000 15.500 1.3055 0.09208 0.08500 -0.0477 0.0027 1.0000 16.000 1.3004 0.09988 0.09302 -0.0495 0.0028 1.0000 16.500 1.2962 0.10774 0.10109 -0.0516 0.0028 1.0000 17.000 1.2919 0.11578 0.10935 -0.0541 0.0029 1.0000 17.500 1.2881 0.12390 0.11768 -0.0569 0.0029 1.0000 18.000 1.2841 0.13216 0.12615 -0.0601 0.0030 1.0000 18.500 1.2796 0.14060 0.13481 -0.0637 0.0031 1.0000 19.000 1.2745 0.14926 0.14367 -0.0676 0.0032 1.0000 19.500 1.2691 0.15803 0.15264 -0.0720 0.0032 1.0000 20.000 1.2648 0.16664 0.16142 -0.0765 0.0033 1.0000 20.500 1.2618 0.17494 0.16987 -0.0810 0.0034 1.0000 21.000 1.2615 0.18261 0.17765 -0.0854 0.0035 1.0000 21.500 1.2656 0.18912 0.18421 -0.0892 0.0036 1.0000 22.000 1.2833 0.19183 0.18684 -0.0907 0.0038 1.0000 22.500 1.2905 0.19794 0.19310 -0.0945 0.0039 1.0000 23.000 1.2983 0.20387 0.19924 -0.0984 0.0041 1.0000 23.500 1.3114 0.20813 0.20365 -0.1011 0.0044 1.0000 24.000 1.3252 0.21181 0.20744 -0.1035 0.0047 1.0000 24.500 1.3504 0.21216 0.20781 -0.1037 0.0051 1.0000 25.000 1.3418 0.22222 0.21821 -0.1108 0.0053 1.0000 25.500 1.3294 0.23327 0.22964 -0.1185 0.0057 1.0000 26.000 1.3130 0.24576 0.24247 -0.1271 0.0059 1.0000 26.500 1.2914 0.26063 0.25764 -0.1370 0.0060 1.0000 27.000 1.2295 0.29663 0.29390 -0.1555 0.0066 1.0000 27.500 0.9620 0.38300 0.38117 -0.1730 0.0159 1.0000 28.000 0.9711 0.38986 0.38808 -0.1748 0.0154 1.0000 28.500 0.9683 0.40531 0.40352 -0.1798 0.0136 1.0000 29.000 0.9734 0.41323 0.41149 -0.1825 0.0129 1.0000 29.500 0.9746 0.42657 0.42483 -0.1862 0.0118 1.0000 30.000 0.9780 0.43609 0.43439 -0.1892 0.0108 1.0000 30.500 0.9830 0.44327 0.44161 -0.1915 0.0104 1.0000 31.000 0.9825 0.45800 0.45635 -0.1955 0.0093 1.0000 31.500 0.9848 0.46746 0.46584 -0.1984 0.0087 1.0000 32.500 0.9878 0.48882 0.48726 -0.2044 0.0080 1.0000 33.000 0.9890 0.49949 0.49796 -0.2073 0.0073 1.0000 33.500 0.9899 0.50897 0.50748 -0.2101 0.0069 1.0000 34.000 0.9907 0.51717 0.51571 -0.2127 0.0066 1.0000 34.500 0.9905 0.52851 0.52708 -0.2156 0.0065 1.0000 35.000 0.9904 0.53968 0.53828 -0.2185 0.0063 1.0000 35.500 0.9900 0.54985 0.54848 -0.2212 0.0061 1.0000 36.000 0.9893 0.55990 0.55856 -0.2239 0.0057 1.0000 36.500 0.9882 0.56912 0.56782 -0.2265 0.0056 1.0000 37.000 0.9868 0.57809 0.57683 -0.2291 0.0054 1.0000 37.500 0.9851 0.58700 0.58577 -0.2316 0.0053 1.0000 38.000 0.9829 0.59507 0.59388 -0.2341 0.0051 1.0000 39.000 0.9778 0.61268 0.61155 -0.2389 0.0050 1.0000 39.500 0.9747 0.62162 0.62053 -0.2414 0.0050 1.0000 40.000 0.9715 0.63091 0.62985 -0.2438 0.0050 1.0000 40.500 0.9680 0.63936 0.63834 -0.2461 0.0050 1.0000 41.000 0.9642 0.64784 0.64686 -0.2484 0.0049 1.0000 41.500 0.9603 0.65615 0.65520 -0.2506 0.0048 1.0000 42.000 0.9559 0.66385 0.66294 -0.2528 0.0046 1.0000 42.500 0.9512 0.67145 0.67057 -0.2549 0.0044 1.0000 43.000 0.9463 0.67864 0.67779 -0.2570 0.0042 1.0000 43.500 0.9409 0.68514 0.68433 -0.2590 0.0040 1.0000 44.000 0.9349 0.69033 0.68956 -0.2610 0.0038 1.0000 44.500 0.9292 0.69855 0.69780 -0.2629 0.0037 1.0000 45.000 0.9241 0.70730 0.70658 -0.2647 0.0036 1.0000 45.500 0.9182 0.71429 0.71360 -0.2665 0.0033 1.0000 46.000 0.9116 0.72002 0.71935 -0.2682 0.0031 1.0000 46.500 0.9047 0.72483 0.72419 -0.2700 0.0028 1.0000 47.000 0.8971 0.72861 0.72801 -0.2718 0.0027 1.0000 48.000 0.8834 0.74191 0.74135 -0.2748 0.0026 1.0000 48.500 0.8762 0.74720 0.74667 -0.2763 0.0024 1.0000 49.000 0.8684 0.75149 0.75099 -0.2777 0.0021 1.0000 49.500 0.8602 0.75469 0.75421 -0.2791 0.0020 1.0000 50.000 0.8517 0.75719 0.75674 -0.2806 0.0019 1.0000 50.500 0.8424 0.75865 0.75823 -0.2820 0.0018 1.0000 51.500 0.8258 0.76702 0.76663 -0.2843 0.0017 1.0000 52.000 0.8173 0.76998 0.76961 -0.2853 0.0016 1.0000 52.500 0.8083 0.77186 0.77151 -0.2864 0.0015 1.0000 53.000 0.7989 0.77295 0.77262 -0.2874 0.0013 1.0000 53.500 0.7891 0.77314 0.77284 -0.2884 0.0012 1.0000 54.000 0.7792 0.77272 0.77244 -0.2895 0.0011 1.0000 54.500 0.7687 0.77133 0.77107 -0.2905 0.0011 1.0000 56.000 0.7381 0.77008 0.76987 -0.2928 0.0010 1.0000 56.500 0.7279 0.76879 0.76860 -0.2934 0.0010 1.0000 57.000 0.7176 0.76708 0.76691 -0.2940 0.0010 1.0000 57.500 0.7071 0.76482 0.76466 -0.2945 0.0009 1.0000 58.000 0.6963 0.76178 0.76165 -0.2950 0.0009 1.0000 58.500 0.6853 0.75831 0.75819 -0.2954 0.0008 1.0000 59.000 0.6742 0.75424 0.75414 -0.2959 0.0007 1.0000 59.500 0.6629 0.74951 0.74942 -0.2962 0.0007 1.0000 60.000 0.6514 0.74436 0.74429 -0.2965 0.0006 1.0000