XFOIL Version 6.94 Calculated polar for: GOE 526 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.4260 0.00948 0.00281 -0.0810 0.6929 0.2120 0.500 0.4750 0.00915 0.00270 -0.0793 0.6758 0.2900 1.500 0.6639 0.00806 0.00331 -0.0944 0.6284 0.9823 2.000 0.7750 0.00824 0.00329 -0.1059 0.5907 0.9997 2.500 0.8156 0.00850 0.00334 -0.1026 0.5489 1.0000 3.000 0.8510 0.00891 0.00350 -0.0984 0.5025 1.0000 3.500 0.8871 0.00935 0.00374 -0.0944 0.4693 1.0000 4.000 0.9243 0.00976 0.00403 -0.0906 0.4449 1.0000 4.500 0.9551 0.01034 0.00436 -0.0856 0.4059 1.0000 5.000 0.9892 0.01079 0.00470 -0.0813 0.3803 1.0000 5.500 1.0235 0.01121 0.00503 -0.0769 0.3566 1.0000 6.000 1.0497 0.01186 0.00544 -0.0712 0.3092 1.0000 6.500 1.0751 0.01254 0.00592 -0.0654 0.2683 1.0000 7.500 1.0980 0.01475 0.00752 -0.0492 0.1654 1.0000 8.000 1.1154 0.01603 0.00858 -0.0429 0.1292 1.0000 8.500 1.1356 0.01736 0.00967 -0.0375 0.0913 1.0000 9.000 1.1556 0.01885 0.01102 -0.0326 0.0681 1.0000 9.500 1.1791 0.02028 0.01241 -0.0285 0.0540 1.0000 10.000 1.1934 0.02241 0.01440 -0.0238 0.0313 1.0000 10.500 1.2123 0.02445 0.01641 -0.0201 0.0208 1.0000 11.000 1.2193 0.02752 0.01946 -0.0159 0.0028 1.0000 11.500 1.2398 0.02980 0.02184 -0.0133 0.0025 1.0000 12.000 1.2591 0.03230 0.02446 -0.0109 0.0024 1.0000 12.500 1.2758 0.03513 0.02743 -0.0088 0.0023 1.0000 13.000 1.2899 0.03835 0.03080 -0.0069 0.0022 1.0000 13.500 1.3007 0.04205 0.03467 -0.0052 0.0022 1.0000 14.000 1.3092 0.04620 0.03900 -0.0040 0.0021 1.0000 14.500 1.3141 0.05096 0.04395 -0.0032 0.0021 1.0000 15.000 1.3160 0.05635 0.04953 -0.0030 0.0021 1.0000 15.500 1.3148 0.06238 0.05578 -0.0032 0.0021 1.0000 16.000 1.3107 0.06908 0.06269 -0.0040 0.0021 1.0000 16.500 1.3037 0.07646 0.07030 -0.0054 0.0021 1.0000 17.000 1.2947 0.08431 0.07838 -0.0072 0.0021 1.0000 17.500 1.2807 0.09315 0.08745 -0.0097 0.0021 1.0000 18.000 1.2652 0.10237 0.09690 -0.0125 0.0021 1.0000 18.500 1.2489 0.11200 0.10675 -0.0159 0.0021 1.0000 19.000 1.2295 0.12236 0.11735 -0.0199 0.0021 1.0000 19.500 1.2111 0.13290 0.12811 -0.0244 0.0022 1.0000 20.000 1.1898 0.14436 0.13980 -0.0299 0.0022 1.0000 20.500 1.1674 0.15655 0.15221 -0.0361 0.0022 1.0000 21.000 1.1500 0.16819 0.16406 -0.0425 0.0022 1.0000 21.500 1.1307 0.18070 0.17677 -0.0497 0.0022 1.0000 22.000 1.1111 0.19389 0.19015 -0.0576 0.0023 1.0000 22.500 1.0950 0.20693 0.20336 -0.0656 0.0023 1.0000 23.000 1.0820 0.21991 0.21650 -0.0736 0.0023 1.0000 23.500 1.0776 0.23077 0.22746 -0.0804 0.0024 1.0000 24.000 1.0806 0.23933 0.23608 -0.0862 0.0024 1.0000 24.500 1.0894 0.24583 0.24262 -0.0909 0.0025 1.0000 25.000 1.0994 0.25181 0.24864 -0.0955 0.0025 1.0000 25.500 1.1118 0.25679 0.25364 -0.0996 0.0025 1.0000 26.000 1.1238 0.26182 0.25871 -0.1038 0.0026 1.0000 26.500 1.1368 0.26634 0.26326 -0.1079 0.0026 1.0000 27.000 1.1481 0.27145 0.26843 -0.1123 0.0026 1.0000 27.500 1.1581 0.27699 0.27402 -0.1170 0.0027 1.0000 28.000 1.1666 0.28311 0.28023 -0.1221 0.0028 1.0000 28.500 1.1731 0.29014 0.28736 -0.1277 0.0029 1.0000 29.000 1.1750 0.29940 0.29674 -0.1344 0.0030 1.0000 30.000 0.8732 0.38122 0.37956 -0.1484 0.0095 1.0000 30.500 0.8758 0.39314 0.39150 -0.1522 0.0086 1.0000 31.000 0.8801 0.40158 0.39997 -0.1556 0.0083 1.0000 31.500 0.8843 0.40964 0.40805 -0.1589 0.0079 1.0000 32.000 0.8888 0.41638 0.41481 -0.1619 0.0076 1.0000 32.500 0.8921 0.42505 0.42351 -0.1651 0.0075 1.0000 33.000 0.8936 0.43671 0.43519 -0.1688 0.0073 1.0000 33.500 0.8961 0.44589 0.44440 -0.1720 0.0070 1.0000 34.000 0.8984 0.45456 0.45310 -0.1752 0.0067 1.0000 34.500 0.9004 0.46287 0.46144 -0.1783 0.0065 1.0000 35.000 0.9021 0.47104 0.46963 -0.1815 0.0063 1.0000 35.500 0.9035 0.47877 0.47739 -0.1845 0.0061 1.0000 36.000 0.9045 0.48618 0.48484 -0.1876 0.0060 1.0000 36.500 0.9053 0.49327 0.49195 -0.1905 0.0059 1.0000 37.500 0.9053 0.50997 0.50871 -0.1965 0.0058 1.0000 38.000 0.9047 0.51805 0.51682 -0.1994 0.0058 1.0000 38.500 0.9039 0.52654 0.52534 -0.2024 0.0058 1.0000 39.000 0.9029 0.53474 0.53357 -0.2053 0.0058 1.0000 39.500 0.9017 0.54293 0.54179 -0.2081 0.0056 1.0000 40.000 0.9002 0.55073 0.54962 -0.2108 0.0054 1.0000 40.500 0.8983 0.55805 0.55697 -0.2135 0.0050 1.0000 41.000 0.8961 0.56470 0.56365 -0.2162 0.0047 1.0000 41.500 0.8934 0.57053 0.56951 -0.2189 0.0045 1.0000 42.500 0.8875 0.58693 0.58596 -0.2239 0.0043 1.0000 43.000 0.8845 0.59488 0.59394 -0.2263 0.0038 1.0000 43.500 0.8808 0.60115 0.60024 -0.2288 0.0035 1.0000 44.000 0.8766 0.60625 0.60537 -0.2313 0.0033 1.0000 44.500 0.8720 0.61027 0.60942 -0.2337 0.0032 1.0000 45.000 0.8680 0.62056 0.61973 -0.2359 0.0031 1.0000 45.500 0.8637 0.62794 0.62714 -0.2380 0.0027 1.0000 46.000 0.8587 0.63346 0.63268 -0.2402 0.0024 1.0000 46.500 0.8532 0.63783 0.63708 -0.2424 0.0023 1.0000 47.000 0.8471 0.64083 0.64011 -0.2447 0.0021 1.0000 47.500 0.8414 0.64759 0.64688 -0.2467 0.0021 1.0000 48.000 0.8362 0.65507 0.65438 -0.2485 0.0020 1.0000 48.500 0.8302 0.66045 0.65979 -0.2503 0.0018 1.0000 49.000 0.8238 0.66440 0.66376 -0.2522 0.0015 1.0000 49.500 0.8168 0.66735 0.66673 -0.2541 0.0014 1.0000 50.000 0.8093 0.66890 0.66831 -0.2561 0.0013 1.0000 51.000 0.7950 0.67751 0.67696 -0.2594 0.0012 1.0000 51.500 0.7879 0.68200 0.68147 -0.2609 0.0012 1.0000 52.000 0.7806 0.68558 0.68507 -0.2623 0.0011 1.0000 52.500 0.7727 0.68769 0.68720 -0.2638 0.0009 1.0000 53.000 0.7645 0.68915 0.68868 -0.2653 0.0008 1.0000 53.500 0.7560 0.69005 0.68961 -0.2668 0.0007 1.0000 54.000 0.7472 0.69002 0.68959 -0.2682 0.0006 1.0000 54.500 0.7380 0.68917 0.68877 -0.2697 0.0006 1.0000 55.500 0.7205 0.69183 0.69145 -0.2720 0.0005 1.0000 56.000 0.7117 0.69226 0.69191 -0.2730 0.0004 1.0000 56.500 0.7022 0.69106 0.69072 -0.2741 0.0003 1.0000 57.000 0.6924 0.68892 0.68860 -0.2752 0.0003 1.0000 58.500 0.6633 0.68453 0.68426 -0.2779 0.0002 1.0000 59.000 0.6533 0.68187 0.68161 -0.2787 0.0001 1.0000 59.500 0.6430 0.67851 0.67827 -0.2795 0.0000 1.0000 60.000 0.6325 0.67420 0.67397 -0.2802 0.0000 1.0000