XFOIL Version 6.94 Calculated polar for: EPPLER 583 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 0.4836 0.01160 0.00641 -0.0908 0.6468 0.8488 0.500 0.5371 0.01177 0.00651 -0.0907 0.6417 0.8567 1.000 0.5915 0.01170 0.00642 -0.0911 0.6362 0.8612 1.500 0.6446 0.01164 0.00632 -0.0909 0.6304 0.8647 2.000 0.7011 0.01167 0.00626 -0.0915 0.6248 0.8680 2.500 0.7555 0.01179 0.00639 -0.0919 0.6188 0.8720 3.000 0.8096 0.01175 0.00636 -0.0922 0.6119 0.8755 3.500 0.8674 0.01173 0.00631 -0.0933 0.6048 0.8787 4.000 0.9203 0.01177 0.00634 -0.0933 0.5973 0.8819 4.500 0.9680 0.01169 0.00635 -0.0922 0.5891 0.8853 5.000 1.0205 0.01165 0.00632 -0.0921 0.5806 0.8889 5.500 1.0703 0.01173 0.00647 -0.0915 0.5713 0.8932 6.000 1.1188 0.01172 0.00651 -0.0908 0.5604 0.8974 6.500 1.1621 0.01173 0.00660 -0.0888 0.5492 0.9016 7.000 1.2005 0.01174 0.00668 -0.0859 0.5356 0.9069 7.500 1.2325 0.01184 0.00689 -0.0818 0.5205 0.9133 8.000 1.2586 0.01204 0.00715 -0.0767 0.5039 0.9210 8.500 1.2816 0.01243 0.00757 -0.0711 0.4850 0.9305 9.000 1.2980 0.01297 0.00816 -0.0647 0.4637 0.9429 9.500 1.3136 0.01379 0.00905 -0.0588 0.4391 0.9649 10.000 1.3413 0.01510 0.01038 -0.0565 0.4101 1.0000 10.500 1.3535 0.01705 0.01226 -0.0522 0.3804 1.0000 11.000 1.3605 0.01944 0.01461 -0.0476 0.3504 1.0000 11.500 1.3621 0.02236 0.01747 -0.0429 0.3187 1.0000 12.000 1.3585 0.02587 0.02088 -0.0382 0.2877 1.0000 12.500 1.3568 0.02956 0.02451 -0.0344 0.2564 1.0000 13.500 1.3544 0.03776 0.03258 -0.0283 0.1998 1.0000 14.000 1.3539 0.04222 0.03699 -0.0261 0.1741 1.0000 14.500 1.3532 0.04699 0.04171 -0.0243 0.1498 1.0000 15.000 1.3521 0.05205 0.04673 -0.0230 0.1254 1.0000 15.500 1.3503 0.05750 0.05213 -0.0222 0.1032 1.0000 16.000 1.3454 0.06357 0.05813 -0.0218 0.0806 1.0000 16.500 1.3431 0.06969 0.06424 -0.0220 0.0645 1.0000 17.000 1.3397 0.07625 0.07082 -0.0226 0.0509 1.0000 17.500 1.3358 0.08318 0.07780 -0.0238 0.0404 1.0000 18.000 1.3323 0.09036 0.08506 -0.0255 0.0317 1.0000 18.500 1.3273 0.09799 0.09281 -0.0276 0.0256 1.0000 19.000 1.3219 0.10592 0.10088 -0.0302 0.0213 1.0000 19.500 1.3154 0.11416 0.10928 -0.0333 0.0177 1.0000 20.000 1.3078 0.12271 0.11799 -0.0369 0.0147 1.0000 20.500 1.2987 0.13163 0.12708 -0.0410 0.0120 1.0000 21.000 1.2870 0.14107 0.13668 -0.0457 0.0099 1.0000 21.500 1.2737 0.15084 0.14662 -0.0509 0.0080 1.0000 22.000 1.2594 0.16086 0.15679 -0.0566 0.0065 1.0000 22.500 1.2494 0.17016 0.16630 -0.0621 0.0053 1.0000 23.000 1.2330 0.18070 0.17698 -0.0686 0.0045 1.0000 23.500 1.2246 0.18979 0.18625 -0.0744 0.0039 1.0000 24.000 1.2167 0.19876 0.19537 -0.0804 0.0036 1.0000 24.500 1.2093 0.20761 0.20432 -0.0864 0.0033 1.0000 25.000 1.2045 0.21571 0.21252 -0.0920 0.0031 1.0000 25.500 1.2020 0.22354 0.22050 -0.0976 0.0029 1.0000 26.000 1.1995 0.23131 0.22844 -0.1032 0.0028 1.0000 26.500 1.1960 0.23933 0.23661 -0.1090 0.0027 1.0000 27.000 1.1903 0.24802 0.24547 -0.1151 0.0027 1.0000 27.500 1.1788 0.25862 0.25627 -0.1221 0.0026 1.0000 29.500 1.1118 0.33195 0.32970 -0.1500 0.0073 1.0000 30.000 1.1215 0.33648 0.33425 -0.1539 0.0068 1.0000 30.500 1.1318 0.33982 0.33761 -0.1576 0.0065 1.0000 31.000 1.1392 0.34661 0.34437 -0.1620 0.0061 1.0000 31.500 1.1480 0.35201 0.34978 -0.1661 0.0053 1.0000 32.000 1.1567 0.35598 0.35377 -0.1701 0.0050 1.0000 32.500 1.1654 0.35889 0.35669 -0.1739 0.0047 1.0000 33.000 1.1744 0.36259 0.36042 -0.1775 0.0046 1.0000 33.500 1.1811 0.37046 0.36825 -0.1823 0.0039 1.0000 34.000 1.1887 0.37428 0.37209 -0.1863 0.0035 1.0000 34.500 1.1958 0.37755 0.37537 -0.1904 0.0033 1.0000 35.000 1.2028 0.37991 0.37777 -0.1941 0.0032 1.0000 35.500 1.2093 0.38557 0.38340 -0.1985 0.0031 1.0000 36.000 1.2168 0.39094 0.38877 -0.2026 0.0027 1.0000 36.500 1.2231 0.39464 0.39249 -0.2068 0.0026 1.0000 37.000 1.2290 0.39822 0.39608 -0.2109 0.0023 1.0000 37.500 1.2345 0.40133 0.39921 -0.2151 0.0022 1.0000 38.000 1.2391 0.40387 0.40177 -0.2192 0.0020 1.0000 38.500 1.2435 0.40599 0.40391 -0.2234 0.0020 1.0000 39.500 1.2517 0.41052 0.40847 -0.2315 0.0019 1.0000