XFOIL Version 6.94 Calculated polar for: EPPLER 433 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 0.5034 0.01326 0.00814 -0.1125 0.7921 0.8467 0.500 0.5461 0.01327 0.00812 -0.1104 0.7810 0.8548 1.000 0.6114 0.01297 0.00771 -0.1126 0.7730 0.8597 1.500 0.6621 0.01286 0.00757 -0.1118 0.7633 0.8649 2.000 0.7186 0.01262 0.00731 -0.1122 0.7524 0.8699 2.500 0.7781 0.01249 0.00714 -0.1134 0.7419 0.8756 3.000 0.8320 0.01223 0.00688 -0.1133 0.7292 0.8801 3.500 0.8802 0.01210 0.00680 -0.1119 0.7154 0.8855 4.000 0.9399 0.01191 0.00657 -0.1129 0.7011 0.8913 4.500 0.9856 0.01180 0.00653 -0.1112 0.6828 0.8977 5.000 1.0248 0.01172 0.00651 -0.1080 0.6625 0.9046 5.500 1.0671 0.01173 0.00655 -0.1055 0.6390 0.9124 6.000 1.0989 0.01176 0.00657 -0.1008 0.6121 0.9224 6.500 1.1196 0.01195 0.00681 -0.0942 0.5801 0.9355 7.000 1.1402 0.01230 0.00711 -0.0876 0.5441 0.9537 7.500 1.1722 0.01298 0.00772 -0.0842 0.4999 1.0000 8.000 1.2011 0.01415 0.00876 -0.0810 0.4525 1.0000 8.500 1.2244 0.01561 0.01006 -0.0770 0.4049 1.0000 9.000 1.2436 0.01730 0.01161 -0.0726 0.3594 1.0000 9.500 1.2600 0.01921 0.01338 -0.0680 0.3159 1.0000 10.000 1.2742 0.02137 0.01541 -0.0634 0.2742 1.0000 10.500 1.2870 0.02379 0.01768 -0.0591 0.2344 1.0000 11.000 1.3004 0.02636 0.02016 -0.0552 0.1962 1.0000 11.500 1.3137 0.02913 0.02286 -0.0517 0.1621 1.0000 12.000 1.3253 0.03221 0.02588 -0.0485 0.1320 1.0000 12.500 1.3350 0.03566 0.02928 -0.0455 0.1057 1.0000 13.000 1.3424 0.03954 0.03314 -0.0428 0.0838 1.0000 13.500 1.3477 0.04389 0.03750 -0.0404 0.0664 1.0000 14.000 1.3499 0.04882 0.04247 -0.0385 0.0534 1.0000 14.500 1.3517 0.05414 0.04787 -0.0373 0.0434 1.0000 15.000 1.3549 0.05964 0.05351 -0.0367 0.0352 1.0000 15.500 1.3563 0.06567 0.05966 -0.0368 0.0288 1.0000 16.000 1.3577 0.07204 0.06622 -0.0374 0.0235 1.0000 16.500 1.3548 0.07939 0.07378 -0.0387 0.0194 1.0000 17.000 1.3475 0.08776 0.08238 -0.0409 0.0162 1.0000 17.500 1.3358 0.09728 0.09214 -0.0440 0.0132 1.0000 18.000 1.3197 0.10795 0.10306 -0.0482 0.0108 1.0000 18.500 1.3011 0.11939 0.11472 -0.0534 0.0091 1.0000 19.000 1.2852 0.13065 0.12624 -0.0591 0.0077 1.0000 19.500 1.2679 0.14226 0.13810 -0.0654 0.0067 1.0000 20.000 1.2564 0.15288 0.14894 -0.0716 0.0061 1.0000 20.500 1.2450 0.16348 0.15969 -0.0781 0.0056 1.0000 21.000 1.2354 0.17357 0.16997 -0.0844 0.0052 1.0000 21.500 1.2260 0.18402 0.18068 -0.0912 0.0049 1.0000 22.000 1.2160 0.19474 0.19163 -0.0983 0.0048 1.0000 22.500 1.2029 0.20658 0.20372 -0.1062 0.0046 1.0000 23.000 1.1843 0.22047 0.21786 -0.1154 0.0047 1.0000 23.500 1.1480 0.24133 0.23899 -0.1277 0.0051 1.0000 25.000 1.1109 0.30041 0.29780 -0.1517 0.0137 1.0000 25.500 1.1223 0.30636 0.30375 -0.1559 0.0127 1.0000 26.000 1.1353 0.31083 0.30824 -0.1593 0.0121 1.0000 26.500 1.1467 0.31674 0.31415 -0.1632 0.0118 1.0000 27.000 1.1550 0.32425 0.32163 -0.1686 0.0108 1.0000 27.500 1.1660 0.32943 0.32681 -0.1726 0.0102 1.0000 28.000 1.1773 0.33373 0.33113 -0.1764 0.0097 1.0000 28.500 1.1898 0.33832 0.33575 -0.1795 0.0095 1.0000 29.000 1.1971 0.34533 0.34273 -0.1851 0.0090 1.0000 29.500 1.2072 0.35041 0.34782 -0.1893 0.0083 1.0000 30.000 1.2170 0.35496 0.35238 -0.1934 0.0079 1.0000 30.500 1.2265 0.35904 0.35648 -0.1973 0.0075 1.0000 31.500 1.2445 0.36795 0.36540 -0.2053 0.0072 1.0000 32.000 1.2534 0.37340 0.37085 -0.2099 0.0068 1.0000 32.500 1.2619 0.37778 0.37525 -0.2140 0.0063 1.0000 33.000 1.2697 0.38148 0.37897 -0.2181 0.0057 1.0000 33.500 1.2770 0.38479 0.38230 -0.2221 0.0055 1.0000 34.000 1.2842 0.38854 0.38607 -0.2258 0.0053 1.0000 34.500 1.2920 0.39364 0.39116 -0.2306 0.0051 1.0000 35.000 1.2992 0.39779 0.39532 -0.2347 0.0045 1.0000 35.500 1.3055 0.40131 0.39886 -0.2388 0.0042 1.0000 36.000 1.3111 0.40434 0.40192 -0.2429 0.0039 1.0000 36.500 1.3160 0.40683 0.40444 -0.2466 0.0037 1.0000 37.000 1.3212 0.41016 0.40777 -0.2508 0.0037 1.0000 37.500 1.3270 0.41390 0.41152 -0.2553 0.0036 1.0000 38.000 1.3328 0.41731 0.41494 -0.2595 0.0034 1.0000 38.500 1.3372 0.41998 0.41763 -0.2636 0.0032 1.0000