XFOIL Version 6.96 Calculated polar for: NACA 0018 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -14.000 -0.6823 0.11378 0.10456 -0.0245 1.0000 0.1321 -13.750 -0.8312 0.08288 0.07335 -0.0407 1.0000 0.1386 -13.500 -0.9075 0.06950 0.05953 -0.0464 1.0000 0.1404 -13.250 -0.9014 0.06742 0.05747 -0.0462 1.0000 0.1439 -13.000 -0.9034 0.06454 0.05455 -0.0463 1.0000 0.1477 -12.750 -0.9242 0.05981 0.04959 -0.0466 1.0000 0.1512 -12.500 -0.9479 0.05528 0.04475 -0.0461 1.0000 0.1546 -12.250 -0.9296 0.05457 0.04419 -0.0453 1.0000 0.1593 -12.000 -0.9334 0.05212 0.04163 -0.0442 1.0000 0.1640 -11.750 -0.9470 0.04909 0.03831 -0.0424 1.0000 0.1686 -11.500 -0.9309 0.04826 0.03763 -0.0413 1.0000 0.1739 -11.250 -0.9320 0.04640 0.03565 -0.0394 1.0000 0.1795 -11.000 -0.9316 0.04468 0.03384 -0.0372 1.0000 0.1852 -10.750 -0.9228 0.04362 0.03283 -0.0353 1.0000 0.1913 -10.500 -0.9266 0.04200 0.03102 -0.0322 1.0000 0.1978 -10.250 -0.9162 0.04112 0.03024 -0.0302 1.0000 0.2042 -10.000 -0.9145 0.03998 0.02904 -0.0270 1.0000 0.2113 -9.750 -0.9081 0.03896 0.02802 -0.0244 1.0000 0.2185 -9.500 -0.9012 0.03805 0.02711 -0.0217 1.0000 0.2264 -9.250 -0.8952 0.03708 0.02610 -0.0188 1.0000 0.2345 -9.000 -0.8869 0.03630 0.02535 -0.0161 1.0000 0.2430 -8.750 -0.8797 0.03544 0.02448 -0.0132 1.0000 0.2519 -8.500 -0.8711 0.03472 0.02378 -0.0104 1.0000 0.2613 -8.250 -0.8619 0.03400 0.02308 -0.0077 1.0000 0.2707 -8.000 -0.8540 0.03329 0.02232 -0.0047 1.0000 0.2813 -7.750 -0.8430 0.03271 0.02183 -0.0021 1.0000 0.2912 -7.500 -0.8354 0.03201 0.02105 0.0009 1.0000 0.3027 -7.250 -0.8232 0.03154 0.02069 0.0034 1.0000 0.3134 -7.000 -0.8129 0.03098 0.02013 0.0061 1.0000 0.3249 -6.750 -0.8030 0.03045 0.01957 0.0088 1.0000 0.3375 -6.500 -0.7902 0.03005 0.01927 0.0112 1.0000 0.3491 -6.250 -0.7790 0.02959 0.01881 0.0138 1.0000 0.3620 -6.000 -0.7675 0.02917 0.01836 0.0163 1.0000 0.3755 -5.750 -0.7537 0.02885 0.01815 0.0185 1.0000 0.3882 -5.500 -0.7408 0.02851 0.01783 0.0207 1.0000 0.4019 -5.250 -0.7283 0.02817 0.01746 0.0230 1.0000 0.4167 -5.000 -0.7135 0.02796 0.01732 0.0250 1.0000 0.4305 -4.750 -0.6987 0.02775 0.01718 0.0269 1.0000 0.4446 -4.500 -0.6605 0.02761 0.01706 0.0244 0.9918 0.4637 -4.250 -0.6221 0.02747 0.01695 0.0219 0.9821 0.4828 -4.000 -0.5845 0.02734 0.01685 0.0197 0.9720 0.5017 -3.750 -0.5459 0.02724 0.01678 0.0174 0.9622 0.5210 -3.500 -0.5074 0.02715 0.01672 0.0152 0.9519 0.5401 -3.250 -0.4727 0.02704 0.01664 0.0138 0.9402 0.5587 -3.000 -0.4338 0.02696 0.01660 0.0117 0.9300 0.5779 -2.750 -0.3969 0.02687 0.01653 0.0101 0.9185 0.5967 -2.500 -0.3629 0.02678 0.01648 0.0090 0.9063 0.6154 -2.250 -0.3183 0.02672 0.01646 0.0063 0.8974 0.6343 -2.000 -0.2854 0.02672 0.01653 0.0058 0.8839 0.6509 -1.750 -0.2467 0.02667 0.01653 0.0043 0.8728 0.6683 -1.500 -0.2093 0.02661 0.01652 0.0032 0.8609 0.6852 -1.250 -0.1773 0.02658 0.01651 0.0029 0.8471 0.7021 -1.000 -0.1375 0.02646 0.01640 0.0015 0.8366 0.7194 -0.750 -0.1074 0.02642 0.01638 0.0017 0.8218 0.7362 -0.500 -0.0710 0.02650 0.01651 0.0011 0.8077 0.7501 -0.250 -0.0312 0.02643 0.01644 -0.0001 0.7957 0.7649 0.000 0.0000 0.02640 0.01641 0.0000 0.7805 0.7806 0.250 0.0312 0.02643 0.01644 0.0001 0.7649 0.7957 0.500 0.0710 0.02650 0.01651 -0.0011 0.7501 0.8077 0.750 0.1074 0.02642 0.01638 -0.0017 0.7362 0.8218 1.000 0.1375 0.02645 0.01640 -0.0015 0.7194 0.8366 1.250 0.1773 0.02658 0.01651 -0.0029 0.7021 0.8471 1.500 0.2093 0.02661 0.01652 -0.0032 0.6852 0.8609 1.750 0.2466 0.02667 0.01653 -0.0043 0.6683 0.8728 2.000 0.2854 0.02671 0.01653 -0.0057 0.6509 0.8839 2.250 0.3183 0.02671 0.01645 -0.0063 0.6343 0.8974 2.500 0.3629 0.02678 0.01647 -0.0090 0.6154 0.9063 2.750 0.3969 0.02686 0.01653 -0.0101 0.5967 0.9185 3.000 0.4337 0.02696 0.01659 -0.0117 0.5779 0.9300 3.250 0.4726 0.02703 0.01664 -0.0138 0.5587 0.9402 3.500 0.5075 0.02714 0.01672 -0.0152 0.5401 0.9519 3.750 0.5458 0.02724 0.01678 -0.0174 0.5210 0.9623 4.000 0.5845 0.02733 0.01685 -0.0197 0.5017 0.9721 4.250 0.6222 0.02746 0.01694 -0.0219 0.4828 0.9822 4.500 0.6605 0.02760 0.01705 -0.0244 0.4637 0.9919 4.750 0.6985 0.02775 0.01717 -0.0268 0.4446 1.0000 5.000 0.7133 0.02795 0.01731 -0.0249 0.4305 1.0000 5.250 0.7281 0.02816 0.01745 -0.0229 0.4167 1.0000 5.500 0.7406 0.02850 0.01782 -0.0207 0.4019 1.0000 5.750 0.7536 0.02885 0.01814 -0.0185 0.3882 1.0000 6.000 0.7673 0.02916 0.01835 -0.0162 0.3755 1.0000 6.250 0.7788 0.02958 0.01880 -0.0138 0.3620 1.0000 6.500 0.7901 0.03004 0.01926 -0.0112 0.3491 1.0000 6.750 0.8029 0.03045 0.01956 -0.0088 0.3375 1.0000 7.000 0.8128 0.03098 0.02012 -0.0061 0.3249 1.0000 7.250 0.8231 0.03153 0.02068 -0.0034 0.3134 1.0000 7.500 0.8353 0.03200 0.02104 -0.0009 0.3027 1.0000 7.750 0.8429 0.03270 0.02182 0.0021 0.2912 1.0000 8.000 0.8539 0.03328 0.02232 0.0047 0.2813 1.0000 8.250 0.8619 0.03399 0.02307 0.0077 0.2707 1.0000 8.500 0.8711 0.03472 0.02377 0.0104 0.2613 1.0000 8.750 0.8797 0.03544 0.02447 0.0132 0.2518 1.0000 9.000 0.8870 0.03629 0.02535 0.0161 0.2430 1.0000 9.250 0.8953 0.03707 0.02609 0.0188 0.2344 1.0000 9.500 0.9014 0.03804 0.02710 0.0216 0.2263 1.0000 9.750 0.9084 0.03895 0.02801 0.0243 0.2184 1.0000 10.000 0.9148 0.03998 0.02903 0.0270 0.2112 1.0000 10.250 0.9167 0.04111 0.03023 0.0301 0.2041 1.0000 10.500 0.9270 0.04200 0.03102 0.0322 0.1977 1.0000 10.750 0.9234 0.04362 0.03282 0.0353 0.1912 1.0000 11.000 0.9324 0.04466 0.03381 0.0371 0.1851 1.0000 11.250 0.9326 0.04640 0.03565 0.0393 0.1795 1.0000 11.500 0.9319 0.04824 0.03761 0.0412 0.1738 1.0000 11.750 0.9481 0.04907 0.03827 0.0422 0.1685 1.0000 12.000 0.9342 0.05212 0.04163 0.0440 0.1639 1.0000 12.250 0.9309 0.05453 0.04414 0.0451 0.1592 1.0000 12.500 0.9498 0.05521 0.04464 0.0460 0.1545 1.0000 12.750 0.9251 0.05982 0.04961 0.0464 0.1511 1.0000 13.000 0.9050 0.06448 0.05448 0.0461 0.1476 1.0000 13.250 0.9046 0.06718 0.05722 0.0461 0.1438 1.0000 13.500 0.9079 0.06961 0.05964 0.0462 0.1403 1.0000 13.750 0.8310 0.08312 0.07360 0.0404 0.1385 1.0000 14.000 0.6851 0.11354 0.10433 0.0244 0.1321 1.0000