XFOIL Version 6.94 Calculated polar for: EPPLER E854 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 0.4832 0.01021 0.00359 -0.1164 0.6916 0.6284 0.500 0.5386 0.01035 0.00368 -0.1163 0.6782 0.6431 1.000 0.5933 0.01044 0.00379 -0.1162 0.6652 0.6580 1.500 0.6474 0.01056 0.00398 -0.1160 0.6525 0.6756 2.000 0.7034 0.01076 0.00417 -0.1161 0.6415 0.6953 2.500 0.7556 0.01085 0.00443 -0.1155 0.6295 0.7184 3.000 0.8104 0.01107 0.00476 -0.1153 0.6191 0.7472 3.500 0.8606 0.01114 0.00509 -0.1142 0.6072 0.7826 4.000 0.9086 0.01123 0.00539 -0.1124 0.5941 0.8350 4.500 0.9556 0.01110 0.00551 -0.1100 0.5781 0.9625 5.000 1.0089 0.01126 0.00567 -0.1098 0.5583 1.0000 5.500 1.0575 0.01146 0.00596 -0.1084 0.5398 1.0000 6.000 1.1047 0.01171 0.00630 -0.1068 0.5191 1.0000 6.500 1.1484 0.01198 0.00665 -0.1044 0.4933 1.0000 7.000 1.1862 0.01231 0.00704 -0.1008 0.4558 1.0000 7.500 1.2151 0.01296 0.00759 -0.0956 0.3950 1.0000 8.000 1.2161 0.01457 0.00866 -0.0857 0.2861 1.0000 8.500 1.2100 0.01697 0.01049 -0.0757 0.1852 1.0000 9.000 1.2104 0.01935 0.01252 -0.0675 0.1209 1.0000 9.500 1.2138 0.02180 0.01480 -0.0606 0.0833 1.0000 10.000 1.2184 0.02446 0.01738 -0.0546 0.0590 1.0000 10.500 1.2225 0.02749 0.02040 -0.0496 0.0429 1.0000 11.000 1.2265 0.03093 0.02388 -0.0454 0.0310 1.0000 11.500 1.2261 0.03513 0.02816 -0.0417 0.0227 1.0000 12.000 1.2289 0.03947 0.03262 -0.0391 0.0161 1.0000 12.500 1.2304 0.04428 0.03759 -0.0371 0.0125 1.0000 13.000 1.2285 0.04985 0.04335 -0.0357 0.0105 1.0000 13.500 1.2264 0.05578 0.04939 -0.0349 0.0095 1.0000 14.000 1.2299 0.06156 0.05546 -0.0343 0.0086 1.0000 14.500 1.2341 0.06755 0.06168 -0.0343 0.0079 1.0000 15.000 1.2386 0.07384 0.06814 -0.0347 0.0075 1.0000 15.500 1.2387 0.08133 0.07599 -0.0356 0.0073 1.0000 16.000 1.2292 0.09056 0.08567 -0.0381 0.0072 1.0000 16.500 1.2135 0.10122 0.09677 -0.0420 0.0071 1.0000 17.000 1.1920 0.11344 0.10940 -0.0476 0.0072 1.0000 17.500 1.1681 0.12675 0.12308 -0.0548 0.0072 1.0000 18.000 1.1424 0.14123 0.13789 -0.0634 0.0073 1.0000 18.500 1.1183 0.15630 0.15325 -0.0731 0.0074 1.0000 19.000 0.9893 0.21366 0.21108 -0.1039 0.0119 1.0000 19.500 0.8402 0.25202 0.25009 -0.1301 0.0221 1.0000 20.000 0.8479 0.26101 0.25909 -0.1341 0.0206 1.0000 20.500 0.8608 0.26850 0.26660 -0.1364 0.0199 1.0000 21.000 0.8610 0.28080 0.27890 -0.1424 0.0182 1.0000 21.500 0.8704 0.28901 0.28714 -0.1457 0.0173 1.0000 22.000 0.8765 0.29957 0.29770 -0.1499 0.0166 1.0000 22.500 0.8833 0.30967 0.30782 -0.1539 0.0153 1.0000 23.000 0.8922 0.31810 0.31627 -0.1570 0.0145 1.0000 23.500 0.8987 0.32846 0.32664 -0.1608 0.0141 1.0000 24.000 0.9049 0.33915 0.33734 -0.1648 0.0126 1.0000 24.500 0.9135 0.34745 0.34567 -0.1674 0.0117 1.0000 25.000 0.9183 0.35929 0.35751 -0.1718 0.0110 1.0000 25.500 0.9250 0.36900 0.36725 -0.1751 0.0098 1.0000 26.000 0.9319 0.37839 0.37666 -0.1780 0.0094 1.0000 26.500 0.9368 0.39060 0.38888 -0.1819 0.0087 1.0000 27.000 0.9426 0.40085 0.39915 -0.1852 0.0079 1.0000 27.500 0.9483 0.40995 0.40828 -0.1880 0.0074 1.0000 28.000 0.9529 0.42157 0.41990 -0.1915 0.0073 1.0000 28.500 0.9576 0.43253 0.43088 -0.1948 0.0071 1.0000 29.000 0.9623 0.44341 0.44179 -0.1980 0.0066 1.0000 29.500 0.9665 0.45398 0.45238 -0.2011 0.0061 1.0000 30.000 0.9703 0.46399 0.46241 -0.2041 0.0058 1.0000 30.500 0.9737 0.47392 0.47238 -0.2071 0.0057 1.0000 31.500 0.9793 0.49493 0.49342 -0.2129 0.0055 1.0000 32.000 0.9819 0.50603 0.50454 -0.2160 0.0054 1.0000 32.500 0.9842 0.51658 0.51512 -0.2189 0.0053 1.0000 33.000 0.9862 0.52729 0.52586 -0.2217 0.0050 1.0000 33.500 0.9876 0.53730 0.53589 -0.2245 0.0049 1.0000 34.000 0.9888 0.54758 0.54620 -0.2273 0.0047 1.0000 34.500 0.9895 0.55747 0.55612 -0.2300 0.0046 1.0000 35.000 0.9899 0.56730 0.56597 -0.2327 0.0044 1.0000 35.500 0.9898 0.57689 0.57560 -0.2353 0.0043 1.0000 36.000 0.9895 0.58647 0.58520 -0.2379 0.0042 1.0000 36.500 0.9886 0.59571 0.59447 -0.2405 0.0041 1.0000 37.000 0.9876 0.60489 0.60369 -0.2430 0.0040 1.0000 37.500 0.9860 0.61371 0.61254 -0.2455 0.0040 1.0000 38.000 0.9838 0.62238 0.62123 -0.2478 0.0039 1.0000 40.000 0.9740 0.65761 0.65657 -0.2573 0.0038 1.0000 40.500 0.9709 0.66582 0.66481 -0.2595 0.0038 1.0000 41.000 0.9678 0.67442 0.67344 -0.2616 0.0037 1.0000 41.500 0.9640 0.68217 0.68122 -0.2638 0.0037 1.0000 42.000 0.9600 0.68993 0.68901 -0.2658 0.0035 1.0000 42.500 0.9556 0.69707 0.69617 -0.2678 0.0034 1.0000 43.000 0.9508 0.70412 0.70324 -0.2698 0.0032 1.0000 43.500 0.9458 0.71076 0.70992 -0.2718 0.0031 1.0000 44.000 0.9403 0.71691 0.71609 -0.2736 0.0030 1.0000 44.500 0.9346 0.72274 0.72195 -0.2755 0.0029 1.0000 45.000 0.9287 0.72840 0.72763 -0.2774 0.0028 1.0000 45.500 0.9223 0.73343 0.73268 -0.2791 0.0026 1.0000 46.000 0.9155 0.73801 0.73729 -0.2809 0.0025 1.0000