XFOIL Version 6.94 Calculated polar for: EPPLER 585 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 0.5523 0.01001 0.00501 -0.1168 0.7072 0.8215 0.500 0.6071 0.01004 0.00496 -0.1167 0.6999 0.8277 1.000 0.6623 0.01010 0.00498 -0.1170 0.6918 0.8333 1.500 0.7192 0.01008 0.00490 -0.1177 0.6828 0.8380 2.000 0.7762 0.01012 0.00487 -0.1183 0.6741 0.8421 2.500 0.8272 0.01007 0.00488 -0.1176 0.6645 0.8464 4.000 0.9897 0.01015 0.00492 -0.1179 0.6309 0.8602 4.500 1.0373 0.01016 0.00507 -0.1166 0.6175 0.8649 5.000 1.0865 0.01026 0.00519 -0.1156 0.6025 0.8705 5.500 1.1348 0.01042 0.00534 -0.1146 0.5848 0.8764 6.000 1.1764 0.01055 0.00554 -0.1121 0.5646 0.8822 6.500 1.2144 0.01080 0.00583 -0.1090 0.5415 0.8894 7.000 1.2458 0.01111 0.00618 -0.1046 0.5150 0.8978 7.500 1.2661 0.01155 0.00665 -0.0980 0.4841 0.9098 8.000 1.2798 0.01226 0.00731 -0.0906 0.4495 0.9253 8.500 1.2914 0.01309 0.00815 -0.0832 0.4126 0.9621 9.000 1.3130 0.01453 0.00948 -0.0791 0.3694 1.0000 9.500 1.3264 0.01639 0.01120 -0.0740 0.3269 1.0000 10.000 1.3365 0.01857 0.01324 -0.0688 0.2867 1.0000 10.500 1.3443 0.02108 0.01561 -0.0639 0.2479 1.0000 11.000 1.3512 0.02390 0.01830 -0.0593 0.2122 1.0000 11.500 1.3612 0.02675 0.02108 -0.0556 0.1790 1.0000 12.000 1.3684 0.03002 0.02424 -0.0520 0.1472 1.0000 12.500 1.3729 0.03371 0.02782 -0.0488 0.1159 1.0000 13.000 1.3760 0.03782 0.03180 -0.0460 0.0877 1.0000 13.500 1.3791 0.04220 0.03608 -0.0437 0.0628 1.0000 14.000 1.3820 0.04691 0.04074 -0.0420 0.0438 1.0000 14.500 1.3859 0.05182 0.04568 -0.0408 0.0317 1.0000 15.000 1.3896 0.05709 0.05103 -0.0401 0.0231 1.0000 15.500 1.3907 0.06294 0.05699 -0.0398 0.0164 1.0000 16.000 1.3866 0.06982 0.06400 -0.0402 0.0107 1.0000 16.500 1.3749 0.07818 0.07252 -0.0413 0.0064 1.0000 17.000 1.3633 0.08709 0.08167 -0.0432 0.0047 1.0000 17.500 1.3482 0.09703 0.09185 -0.0462 0.0039 1.0000 18.000 1.3329 0.10749 0.10259 -0.0500 0.0035 1.0000 18.500 1.3190 0.11801 0.11337 -0.0545 0.0032 1.0000 19.000 1.3053 0.12871 0.12432 -0.0595 0.0030 1.0000 19.500 1.2917 0.13951 0.13534 -0.0651 0.0028 1.0000 20.000 1.2790 0.15019 0.14623 -0.0710 0.0027 1.0000 20.500 1.2674 0.16069 0.15693 -0.0771 0.0026 1.0000 21.000 1.2583 0.17060 0.16701 -0.0831 0.0026 1.0000 21.500 1.2506 0.18004 0.17662 -0.0890 0.0025 1.0000 22.000 1.2458 0.18896 0.18571 -0.0948 0.0024 1.0000 22.500 1.2383 0.19856 0.19551 -0.1012 0.0024 1.0000 23.000 1.2299 0.20877 0.20594 -0.1081 0.0024 1.0000 23.500 1.2202 0.21963 0.21701 -0.1155 0.0024 1.0000 24.000 1.2124 0.23041 0.22798 -0.1229 0.0025 1.0000 24.500 1.1982 0.24356 0.24135 -0.1315 0.0025 1.0000 25.500 1.1260 0.30561 0.30346 -0.1547 0.0086 1.0000 26.000 1.1369 0.31151 0.30936 -0.1589 0.0081 1.0000 26.500 1.1486 0.31616 0.31403 -0.1627 0.0076 1.0000 27.000 1.1620 0.31954 0.31744 -0.1657 0.0074 1.0000 27.500 1.1693 0.32774 0.32560 -0.1710 0.0073 1.0000 28.000 1.1790 0.33503 0.33288 -0.1757 0.0065 1.0000 28.500 1.1893 0.34012 0.33797 -0.1798 0.0060 1.0000 29.000 1.1995 0.34446 0.34233 -0.1838 0.0057 1.0000 29.500 1.2101 0.34812 0.34601 -0.1874 0.0055 1.0000 30.000 1.2197 0.35331 0.35121 -0.1913 0.0054 1.0000 30.500 1.2282 0.36026 0.35813 -0.1964 0.0052 1.0000 31.000 1.2376 0.36540 0.36328 -0.2006 0.0046 1.0000 31.500 1.2464 0.36954 0.36743 -0.2047 0.0042 1.0000 32.000 1.2545 0.37304 0.37096 -0.2086 0.0040 1.0000 32.500 1.2633 0.37612 0.37407 -0.2120 0.0038 1.0000 33.000 1.2704 0.38135 0.37929 -0.2167 0.0038 1.0000 33.500 1.2795 0.38759 0.38551 -0.2212 0.0032 1.0000 34.000 1.2868 0.39155 0.38949 -0.2253 0.0029 1.0000 34.500 1.2935 0.39497 0.39293 -0.2294 0.0026 1.0000 35.000 1.2995 0.39800 0.39598 -0.2335 0.0025 1.0000 35.500 1.3053 0.40087 0.39888 -0.2372 0.0024 1.0000 36.000 1.3116 0.40551 0.40350 -0.2416 0.0024 1.0000 36.500 1.3179 0.40975 0.40775 -0.2459 0.0023 1.0000 37.000 1.3245 0.41383 0.41184 -0.2500 0.0022 1.0000 37.500 1.3300 0.41711 0.41512 -0.2541 0.0020 1.0000 38.000 1.3347 0.41988 0.41791 -0.2583 0.0019 1.0000 38.500 1.3391 0.42242 0.42047 -0.2624 0.0018 1.0000