XFOIL Version 6.94 Calculated polar for: EPPLER 551 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 0.4094 0.01278 0.00561 -0.0940 0.6373 0.5612 0.500 0.4649 0.01274 0.00552 -0.0942 0.6269 0.5669 1.000 0.5220 0.01284 0.00558 -0.0947 0.6175 0.5722 1.500 0.5761 0.01289 0.00570 -0.0946 0.6082 0.5783 2.000 0.6328 0.01300 0.00573 -0.0951 0.5990 0.5848 2.500 0.6874 0.01312 0.00596 -0.0952 0.5903 0.5917 3.000 0.7416 0.01323 0.00613 -0.0951 0.5809 0.5996 3.500 0.7991 0.01352 0.00635 -0.0958 0.5719 0.6076 4.000 0.8497 0.01355 0.00661 -0.0950 0.5622 0.6160 4.500 0.9051 0.01373 0.00678 -0.0951 0.5523 0.6261 5.000 0.9554 0.01388 0.00714 -0.0944 0.5418 0.6369 5.500 1.0083 0.01403 0.00735 -0.0940 0.5310 0.6498 6.000 1.0573 0.01422 0.00774 -0.0930 0.5195 0.6633 6.500 1.1074 0.01433 0.00795 -0.0920 0.5067 0.6789 7.000 1.1515 0.01448 0.00835 -0.0900 0.4930 0.6975 7.500 1.1962 0.01466 0.00868 -0.0881 0.4783 0.7204 8.000 1.2348 0.01480 0.00902 -0.0850 0.4613 0.7490 8.500 1.2650 0.01496 0.00947 -0.0803 0.4421 0.7859 9.000 1.2805 0.01509 0.00992 -0.0727 0.4211 0.8508 9.500 1.2974 0.01553 0.01050 -0.0661 0.3943 1.0000 10.000 1.3100 0.01660 0.01154 -0.0597 0.3604 1.0000 10.500 1.3109 0.01839 0.01319 -0.0525 0.3207 1.0000 11.000 1.3053 0.02096 0.01559 -0.0455 0.2808 1.0000 11.500 1.2962 0.02427 0.01876 -0.0395 0.2444 1.0000 12.000 1.2914 0.02790 0.02232 -0.0349 0.2111 1.0000 12.500 1.2842 0.03214 0.02648 -0.0311 0.1819 1.0000 13.000 1.2771 0.03685 0.03112 -0.0282 0.1550 1.0000 13.500 1.2717 0.04187 0.03611 -0.0262 0.1317 1.0000 14.000 1.2659 0.04735 0.04156 -0.0248 0.1112 1.0000 14.500 1.2626 0.05296 0.04717 -0.0241 0.0936 1.0000 15.000 1.2577 0.05911 0.05333 -0.0240 0.0787 1.0000 15.500 1.2541 0.06547 0.05973 -0.0244 0.0662 1.0000 16.000 1.2506 0.07215 0.06647 -0.0252 0.0562 1.0000 16.500 1.2453 0.07937 0.07375 -0.0266 0.0483 1.0000 17.000 1.2402 0.08689 0.08134 -0.0285 0.0418 1.0000 17.500 1.2370 0.09441 0.08899 -0.0307 0.0363 1.0000 18.000 1.2334 0.10225 0.09695 -0.0335 0.0315 1.0000 18.500 1.2286 0.11043 0.10524 -0.0366 0.0277 1.0000 19.000 1.2246 0.11870 0.11366 -0.0402 0.0241 1.0000 19.500 1.2210 0.12706 0.12220 -0.0441 0.0211 1.0000 20.000 1.2165 0.13552 0.13083 -0.0483 0.0187 1.0000 20.500 1.2116 0.14401 0.13943 -0.0529 0.0167 1.0000 21.000 1.2080 0.15243 0.14801 -0.0576 0.0149 1.0000 21.500 1.2049 0.16059 0.15632 -0.0624 0.0135 1.0000 22.000 1.2021 0.16881 0.16469 -0.0675 0.0122 1.0000 22.500 1.2009 0.17645 0.17244 -0.0724 0.0112 1.0000 23.000 1.1942 0.18564 0.18188 -0.0785 0.0104 1.0000 23.500 1.1915 0.19382 0.19018 -0.0841 0.0097 1.0000 24.000 1.1877 0.20210 0.19856 -0.0899 0.0091 1.0000 24.500 1.1729 0.21348 0.21024 -0.0977 0.0089 1.0000 25.000 1.1455 0.22867 0.22575 -0.1079 0.0086 1.0000 27.000 0.8560 0.36154 0.35983 -0.1612 0.0132 1.0000 27.500 0.8626 0.37098 0.36928 -0.1646 0.0123 1.0000 28.000 0.8706 0.37885 0.37718 -0.1676 0.0117 1.0000 28.500 0.8746 0.39077 0.38910 -0.1714 0.0114 1.0000 29.000 0.8796 0.40171 0.40006 -0.1751 0.0107 1.0000 29.500 0.8850 0.41150 0.40987 -0.1784 0.0099 1.0000 30.000 0.8905 0.42037 0.41876 -0.1816 0.0095 1.0000 30.500 0.8973 0.42815 0.42657 -0.1840 0.0092 1.0000 31.000 0.8991 0.44091 0.43933 -0.1881 0.0091 1.0000 31.500 0.9030 0.45180 0.45025 -0.1915 0.0086 1.0000 32.000 0.9067 0.46191 0.46038 -0.1946 0.0081 1.0000 32.500 0.9102 0.47146 0.46995 -0.1977 0.0077 1.0000 33.000 0.9134 0.48075 0.47926 -0.2008 0.0074 1.0000 33.500 0.9164 0.48912 0.48765 -0.2036 0.0072 1.0000 34.500 0.9204 0.50906 0.50763 -0.2096 0.0070 1.0000 35.000 0.9220 0.51953 0.51813 -0.2127 0.0069 1.0000 35.500 0.9234 0.52953 0.52815 -0.2156 0.0068 1.0000 36.000 0.9246 0.53933 0.53798 -0.2184 0.0065 1.0000 36.500 0.9253 0.54847 0.54714 -0.2212 0.0062 1.0000 37.000 0.9257 0.55734 0.55603 -0.2239 0.0058 1.0000 37.500 0.9256 0.56582 0.56454 -0.2266 0.0056 1.0000 38.000 0.9252 0.57375 0.57250 -0.2293 0.0053 1.0000 38.500 0.9245 0.58153 0.58030 -0.2318 0.0052 1.0000 39.500 0.9220 0.60023 0.59904 -0.2370 0.0051 1.0000 40.000 0.9206 0.60933 0.60816 -0.2395 0.0050 1.0000 40.500 0.9189 0.61789 0.61674 -0.2419 0.0048 1.0000 41.000 0.9167 0.62572 0.62460 -0.2443 0.0046 1.0000 41.500 0.9142 0.63344 0.63234 -0.2466 0.0044 1.0000 42.000 0.9112 0.64036 0.63929 -0.2489 0.0043 1.0000 42.500 0.9080 0.64738 0.64633 -0.2512 0.0041 1.0000 43.000 0.9045 0.65388 0.65285 -0.2534 0.0040 1.0000 43.500 0.9005 0.65991 0.65891 -0.2556 0.0038 1.0000 44.000 0.8962 0.66551 0.66453 -0.2577 0.0037 1.0000 44.500 0.8914 0.67040 0.66945 -0.2598 0.0036 1.0000 46.000 0.8767 0.68823 0.68734 -0.2657 0.0035 1.0000 46.500 0.8713 0.69327 0.69241 -0.2676 0.0035 1.0000 47.000 0.8660 0.69863 0.69778 -0.2693 0.0034 1.0000 47.500 0.8601 0.70291 0.70208 -0.2710 0.0033 1.0000 48.000 0.8539 0.70670 0.70590 -0.2727 0.0032 1.0000 48.500 0.8474 0.71010 0.70932 -0.2744 0.0030 1.0000 49.000 0.8406 0.71287 0.71211 -0.2760 0.0029 1.0000 49.500 0.8337 0.71558 0.71485 -0.2776 0.0027 1.0000 50.000 0.8265 0.71766 0.71694 -0.2791 0.0026 1.0000 50.500 0.8189 0.71926 0.71856 -0.2806 0.0025 1.0000 51.000 0.8112 0.72044 0.71976 -0.2820 0.0024 1.0000 51.500 0.8031 0.72104 0.72038 -0.2834 0.0023 1.0000 52.000 0.7947 0.72105 0.72041 -0.2848 0.0022 1.0000 54.000 0.7611 0.72261 0.72204 -0.2894 0.0022 1.0000 54.500 0.7523 0.72197 0.72142 -0.2903 0.0021 1.0000 55.000 0.7433 0.72059 0.72006 -0.2913 0.0021 1.0000 55.500 0.7343 0.71912 0.71860 -0.2922 0.0020 1.0000 56.000 0.7250 0.71708 0.71657 -0.2930 0.0019 1.0000 56.500 0.7155 0.71453 0.71405 -0.2939 0.0018 1.0000 57.000 0.7058 0.71150 0.71103 -0.2946 0.0017 1.0000 57.500 0.6960 0.70816 0.70771 -0.2953 0.0015 1.0000 58.000 0.6860 0.70428 0.70384 -0.2960 0.0015 1.0000 58.500 0.6759 0.69992 0.69949 -0.2966 0.0013 1.0000 59.000 0.6657 0.69490 0.69450 -0.2972 0.0013 1.0000 59.500 0.6552 0.68951 0.68911 -0.2978 0.0012 1.0000