XFOIL Version 6.94 Calculated polar for: EPPLER 664 (EXTENDED) 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 1.0143 0.01871 0.01239 -0.2186 0.7111 0.7634 0.500 1.0779 0.01889 0.01265 -0.2212 0.7043 0.7683 1.000 1.1430 0.01886 0.01269 -0.2241 0.6960 0.7725 1.500 1.2107 0.01887 0.01267 -0.2275 0.6882 0.7766 2.000 1.2728 0.01872 0.01268 -0.2296 0.6784 0.7793 2.500 1.3365 0.01838 0.01240 -0.2316 0.6681 0.7827 3.000 1.3979 0.01821 0.01241 -0.2333 0.6558 0.7856 3.500 1.4616 0.01785 0.01209 -0.2353 0.6424 0.7883 4.000 1.5220 0.01745 0.01185 -0.2365 0.6239 0.7917 4.500 1.5802 0.01719 0.01180 -0.2372 0.5966 0.7942 5.000 1.6332 0.01717 0.01171 -0.2367 0.5415 0.7961 5.500 1.6568 0.01914 0.01285 -0.2299 0.4169 0.7986 6.000 1.6684 0.02183 0.01497 -0.2212 0.3180 0.8010 7.000 1.6682 0.02795 0.02060 -0.2002 0.2026 0.8051 7.500 1.6699 0.03200 0.02446 -0.1924 0.1570 0.8073 8.000 1.6743 0.03647 0.02880 -0.1865 0.1203 0.8100 8.500 1.6822 0.04104 0.03329 -0.1819 0.0905 0.8129 9.000 1.6897 0.04582 0.03801 -0.1777 0.0666 0.8149 9.500 1.6974 0.05068 0.04287 -0.1740 0.0497 0.8169 10.000 1.7046 0.05566 0.04791 -0.1704 0.0368 0.8194 10.500 1.7084 0.06117 0.05350 -0.1669 0.0254 0.8221 11.000 1.7019 0.06803 0.06046 -0.1628 0.0165 0.8248 11.500 1.6972 0.07508 0.06771 -0.1597 0.0133 0.8277 12.000 1.6907 0.08264 0.07552 -0.1572 0.0119 0.8308 12.500 1.6863 0.09028 0.08341 -0.1556 0.0110 0.8341 13.000 1.6783 0.09866 0.09201 -0.1546 0.0104 0.8374 13.500 1.6669 0.10770 0.10130 -0.1542 0.0100 0.8418 14.000 1.6613 0.11620 0.11009 -0.1545 0.0097 0.8474 14.500 1.6562 0.12470 0.11887 -0.1554 0.0094 0.8536 15.000 1.6529 0.13303 0.12747 -0.1569 0.0092 0.8612 15.500 1.6507 0.14127 0.13601 -0.1589 0.0090 0.8738 16.500 1.6453 0.15776 0.15314 -0.1648 0.0088 1.0048 17.000 1.6417 0.16717 0.16286 -0.1698 0.0087 1.0048 17.500 1.6347 0.17774 0.17376 -0.1763 0.0087 1.0048 18.000 1.6221 0.19018 0.18657 -0.1849 0.0087 1.0048 18.500 1.6001 0.20608 0.20294 -0.1972 0.0089 1.0048 19.000 1.5665 0.22698 0.22437 -0.2145 0.0091 1.0048 19.500 1.5163 0.25742 0.25534 -0.2402 0.0096 1.0048