XFOIL Version 6.94 Calculated polar for: EPPLER 582 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 0.4536 0.01376 0.00849 -0.0898 0.7304 0.8981 0.500 0.5097 0.01359 0.00817 -0.0898 0.7234 0.9042 1.000 0.5558 0.01359 0.00812 -0.0885 0.7151 0.9102 1.500 0.6059 0.01350 0.00797 -0.0882 0.7058 0.9148 2.000 0.6671 0.01336 0.00769 -0.0898 0.6981 0.9172 2.500 0.7082 0.01325 0.00766 -0.0875 0.6879 0.9206 3.000 0.7656 0.01309 0.00744 -0.0883 0.6788 0.9235 3.500 0.8155 0.01307 0.00744 -0.0879 0.6683 0.9260 4.000 0.8703 0.01291 0.00728 -0.0882 0.6572 0.9289 4.500 0.9214 0.01289 0.00730 -0.0881 0.6454 0.9312 5.000 0.9779 0.01277 0.00719 -0.0888 0.6327 0.9330 5.500 1.0212 0.01270 0.00724 -0.0870 0.6176 0.9358 6.000 1.0663 0.01263 0.00721 -0.0853 0.6020 0.9398 6.500 1.1114 0.01264 0.00725 -0.0838 0.5838 0.9434 7.000 1.1485 0.01272 0.00738 -0.0807 0.5628 0.9481 7.500 1.1767 0.01292 0.00767 -0.0761 0.5391 0.9544 8.000 1.2024 0.01331 0.00815 -0.0712 0.5115 0.9640 8.500 1.2345 0.01401 0.00885 -0.0682 0.4770 0.9813 9.000 1.2620 0.01509 0.00992 -0.0651 0.4384 1.0000 9.500 1.2815 0.01667 0.01141 -0.0611 0.3976 1.0000 10.000 1.2955 0.01872 0.01335 -0.0569 0.3561 1.0000 10.500 1.3046 0.02123 0.01575 -0.0525 0.3150 1.0000 11.000 1.3113 0.02412 0.01852 -0.0484 0.2752 1.0000 11.500 1.3185 0.02723 0.02155 -0.0448 0.2373 1.0000 12.000 1.3252 0.03060 0.02485 -0.0416 0.2025 1.0000 12.500 1.3296 0.03437 0.02855 -0.0387 0.1710 1.0000 13.000 1.3332 0.03848 0.03259 -0.0362 0.1413 1.0000 13.500 1.3363 0.04294 0.03700 -0.0341 0.1134 1.0000 14.000 1.3361 0.04799 0.04199 -0.0325 0.0883 1.0000 14.500 1.3358 0.05342 0.04738 -0.0314 0.0652 1.0000 15.000 1.3332 0.05942 0.05335 -0.0309 0.0470 1.0000 15.500 1.3318 0.06568 0.05965 -0.0310 0.0342 1.0000 16.000 1.3290 0.07248 0.06656 -0.0316 0.0256 1.0000 16.500 1.3227 0.08015 0.07438 -0.0329 0.0189 1.0000 17.000 1.3092 0.08933 0.08372 -0.0352 0.0134 1.0000 17.500 1.2922 0.09956 0.09415 -0.0384 0.0098 1.0000 18.000 1.2763 0.11006 0.10492 -0.0424 0.0082 1.0000 18.500 1.2590 0.12110 0.11618 -0.0472 0.0070 1.0000 19.000 1.2475 0.13132 0.12665 -0.0521 0.0061 1.0000 19.500 1.2360 0.14153 0.13702 -0.0575 0.0056 1.0000 20.000 1.2282 0.15096 0.14664 -0.0626 0.0052 1.0000 20.500 1.2240 0.15980 0.15572 -0.0677 0.0048 1.0000 21.000 1.2203 0.16851 0.16465 -0.0729 0.0046 1.0000 21.500 1.2161 0.17738 0.17373 -0.0785 0.0045 1.0000 22.000 1.2096 0.18691 0.18350 -0.0847 0.0043 1.0000 22.500 1.2000 0.19738 0.19422 -0.0917 0.0043 1.0000 23.000 1.1853 0.20954 0.20666 -0.0998 0.0043 1.0000 23.500 1.1564 0.22663 0.22409 -0.1106 0.0045 1.0000 24.000 1.0973 0.25767 0.25531 -0.1262 0.0054 1.0000 25.500 0.8728 0.33623 0.33463 -0.1480 0.0135 1.0000 26.000 0.8802 0.34612 0.34455 -0.1520 0.0124 1.0000 27.000 0.8927 0.36774 0.36619 -0.1600 0.0113 1.0000 27.500 0.8989 0.37847 0.37695 -0.1639 0.0104 1.0000 28.000 0.9054 0.38805 0.38656 -0.1675 0.0097 1.0000 28.500 0.9122 0.39771 0.39624 -0.1707 0.0094 1.0000 29.000 0.9156 0.41065 0.40919 -0.1751 0.0090 1.0000 29.500 0.9206 0.42158 0.42013 -0.1787 0.0083 1.0000 30.000 0.9253 0.43190 0.43049 -0.1822 0.0078 1.0000 30.500 0.9301 0.44127 0.43988 -0.1855 0.0074 1.0000 31.000 0.9339 0.45225 0.45088 -0.1889 0.0073 1.0000 31.500 0.9373 0.46497 0.46361 -0.1926 0.0063 1.0000 32.000 0.9406 0.47515 0.47382 -0.1959 0.0058 1.0000 32.500 0.9437 0.48413 0.48283 -0.1988 0.0054 1.0000 33.000 0.9459 0.49705 0.49576 -0.2024 0.0053 1.0000 33.500 0.9485 0.50871 0.50744 -0.2056 0.0049 1.0000 34.000 0.9504 0.51939 0.51814 -0.2087 0.0045 1.0000 34.500 0.9520 0.52973 0.52851 -0.2118 0.0042 1.0000 35.000 0.9530 0.53934 0.53815 -0.2147 0.0039 1.0000 36.000 0.9540 0.55960 0.55845 -0.2205 0.0037 1.0000 36.500 0.9542 0.57096 0.56983 -0.2235 0.0037 1.0000 37.000 0.9544 0.58176 0.58065 -0.2264 0.0036 1.0000 37.500 0.9541 0.59204 0.59096 -0.2292 0.0034 1.0000 38.000 0.9532 0.60180 0.60075 -0.2319 0.0032 1.0000 38.500 0.9521 0.61159 0.61057 -0.2345 0.0030 1.0000 39.000 0.9505 0.62077 0.61978 -0.2372 0.0029 1.0000 39.500 0.9485 0.62973 0.62876 -0.2398 0.0028 1.0000 40.000 0.9461 0.63845 0.63751 -0.2423 0.0027 1.0000 40.500 0.9434 0.64686 0.64595 -0.2449 0.0026 1.0000 41.000 0.9403 0.65488 0.65399 -0.2473 0.0025 1.0000 41.500 0.9368 0.66263 0.66177 -0.2497 0.0025 1.0000 42.000 0.9326 0.66998 0.66915 -0.2519 0.0024 1.0000