XFOIL Version 6.96 Calculated polar for: RONCZ 1080 VOYAGER INNER AFT WING AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.750 -0.1298 0.09336 0.08909 -0.0917 0.7734 0.0724 -11.500 -0.2060 0.08982 0.08540 -0.1043 0.7868 0.0714 -11.250 -0.1986 0.08730 0.08288 -0.1046 0.7823 0.0730 -11.000 -0.2025 0.08300 0.07858 -0.1067 0.7786 0.0742 -10.750 -0.2245 0.07573 0.07131 -0.1120 0.7755 0.0769 -10.500 -0.2712 0.06819 0.06366 -0.1168 0.7727 0.0780 -10.250 -0.4750 0.04712 0.04125 -0.1049 0.7699 0.0374 -10.000 -0.4750 0.04456 0.03855 -0.1026 0.7663 0.0371 -9.750 -0.4758 0.04213 0.03593 -0.0999 0.7630 0.0367 -9.500 -0.4761 0.03962 0.03313 -0.0969 0.7601 0.0362 -9.250 -0.4731 0.03683 0.02999 -0.0941 0.7575 0.0352 -9.000 -0.4704 0.03348 0.02604 -0.0908 0.7552 0.0338 -8.750 -0.4595 0.03114 0.02322 -0.0884 0.7526 0.0332 -8.500 -0.4388 0.02947 0.02134 -0.0876 0.7498 0.0333 -8.250 -0.4148 0.02798 0.01972 -0.0873 0.7471 0.0338 -8.000 -0.3893 0.02674 0.01837 -0.0872 0.7445 0.0346 -7.750 -0.3621 0.02555 0.01704 -0.0873 0.7421 0.0354 -7.500 -0.3345 0.02452 0.01587 -0.0874 0.7402 0.0366 -7.250 -0.3071 0.02353 0.01479 -0.0875 0.7385 0.0387 -7.000 -0.2839 0.02288 0.01420 -0.0872 0.7366 0.0411 -6.750 -0.2612 0.02228 0.01354 -0.0865 0.7346 0.0437 -6.500 -0.2415 0.02144 0.01281 -0.0855 0.7326 0.0465 -6.250 -0.2232 0.02095 0.01230 -0.0841 0.7305 0.0508 -6.000 -0.2082 0.02036 0.01179 -0.0823 0.7286 0.0570 -5.750 -0.1933 0.01983 0.01130 -0.0803 0.7268 0.0699 -5.500 -0.1815 0.01913 0.01079 -0.0779 0.7249 0.0951 -5.250 -0.1682 0.01856 0.01042 -0.0757 0.7231 0.1339 -5.000 -0.1549 0.01805 0.01015 -0.0736 0.7215 0.1843 -4.750 -0.1454 0.01750 0.01000 -0.0709 0.7201 0.2596 -4.500 -0.1425 0.01682 0.00992 -0.0672 0.7183 0.3700 -4.250 -0.1431 0.01605 0.00999 -0.0625 0.7164 0.5277 -4.000 -0.1259 0.01653 0.01118 -0.0592 0.7147 0.6800 -3.750 -0.1064 0.01721 0.01181 -0.0571 0.7130 0.7237 -3.500 -0.0844 0.01792 0.01246 -0.0554 0.7112 0.7479 -3.250 -0.0597 0.01863 0.01310 -0.0539 0.7093 0.7653 -3.000 -0.0360 0.01925 0.01363 -0.0525 0.7078 0.7804 -2.750 -0.0058 0.02003 0.01436 -0.0518 0.7066 0.7901 -2.500 0.0199 0.02059 0.01483 -0.0508 0.7053 0.8008 -2.250 0.0463 0.02117 0.01533 -0.0499 0.7042 0.8114 -2.000 0.0782 0.02180 0.01588 -0.0498 0.7032 0.8190 -1.750 0.0856 0.02236 0.01647 -0.0464 0.7007 0.8314 -1.500 0.1240 0.02339 0.01750 -0.0473 0.6987 0.8383 -1.250 0.1373 0.02407 0.01819 -0.0447 0.6965 0.8505 -1.000 0.1840 0.02476 0.01883 -0.0476 0.6947 0.8570 -0.750 0.1941 0.02504 0.01909 -0.0447 0.6923 0.8670 -0.500 0.2397 0.02536 0.01934 -0.0480 0.6910 0.8705 -0.250 0.2375 0.02551 0.01946 -0.0429 0.6891 0.8810 0.000 0.2817 0.02553 0.01941 -0.0460 0.6879 0.8834 0.250 0.3268 0.02558 0.01938 -0.0495 0.6869 0.8854 0.500 0.3669 0.02574 0.01947 -0.0521 0.6857 0.8880 0.750 0.2686 0.02823 0.02225 -0.0326 0.6758 0.9031 1.000 0.2883 0.02840 0.02239 -0.0317 0.6733 0.9072 1.250 0.2820 0.02824 0.02220 -0.0257 0.6711 0.9144 1.500 0.3248 0.02811 0.02201 -0.0286 0.6702 0.9155 1.750 0.3707 0.02789 0.02173 -0.0318 0.6694 0.9164 2.000 0.4155 0.02774 0.02152 -0.0350 0.6686 0.9174 2.250 0.1691 0.03381 0.02792 0.0030 0.6409 0.9453 2.500 0.2057 0.03377 0.02784 0.0013 0.6387 0.9466 2.750 0.2464 0.03357 0.02760 -0.0008 0.6373 0.9477 3.000 0.2879 0.03328 0.02728 -0.0028 0.6363 0.9486 3.250 0.2619 0.03535 0.02939 0.0020 0.6239 0.9564 3.500 0.2933 0.03521 0.02922 0.0014 0.6216 0.9588 3.750 0.3351 0.03490 0.02890 -0.0008 0.6203 0.9595 4.000 0.3774 0.03453 0.02852 -0.0029 0.6193 0.9601 4.250 0.4214 0.03400 0.02799 -0.0051 0.6186 0.9607 4.500 0.4665 0.03338 0.02737 -0.0073 0.6181 0.9612 4.750 0.5140 0.03259 0.02658 -0.0098 0.6178 0.9616 5.000 0.5643 0.03171 0.02571 -0.0127 0.6176 0.9618 5.250 0.4958 0.03739 0.03149 -0.0069 0.5900 0.9741 5.500 0.5389 0.03678 0.03091 -0.0089 0.5884 0.9751 5.750 0.5825 0.03610 0.03025 -0.0110 0.5873 0.9762 6.000 0.6284 0.03515 0.02934 -0.0131 0.5866 0.9771 6.250 0.6760 0.03397 0.02820 -0.0152 0.5862 0.9779 6.500 0.7269 0.03245 0.02672 -0.0175 0.5862 0.9784 6.750 0.7804 0.03088 0.02519 -0.0201 0.5863 0.9786 7.000 0.8394 0.02912 0.02347 -0.0236 0.5862 0.9781 7.250 0.9033 0.02738 0.02176 -0.0282 0.5859 0.9766 7.500 0.9682 0.02565 0.02005 -0.0332 0.5852 0.9750 7.750 0.9521 0.02714 0.02169 -0.0286 0.5726 0.9847 8.000 1.0170 0.02515 0.01974 -0.0331 0.5715 0.9834 8.250 1.0874 0.02320 0.01780 -0.0389 0.5696 0.9806 8.500 1.0890 0.02379 0.01855 -0.0362 0.5586 0.9885 8.750 1.1515 0.02199 0.01678 -0.0409 0.5545 0.9871 9.000 1.1571 0.02226 0.01719 -0.0386 0.5435 0.9963 9.250 1.1908 0.02138 0.01638 -0.0396 0.5348 1.0000 9.500 1.1079 0.02269 0.01767 -0.0234 0.5263 1.0000 9.750 1.0996 0.02375 0.01877 -0.0199 0.5131 1.0000 10.000 1.1055 0.02443 0.01948 -0.0181 0.4985 1.0000 10.250 1.1246 0.02441 0.01947 -0.0174 0.4825 1.0000 10.500 1.1538 0.02376 0.01876 -0.0173 0.4638 1.0000 10.750 1.1702 0.02396 0.01884 -0.0162 0.4385 1.0000 11.000 1.1818 0.02452 0.01921 -0.0146 0.4111 1.0000 11.250 1.1842 0.02574 0.02023 -0.0124 0.3839 1.0000 11.500 1.1807 0.02748 0.02182 -0.0100 0.3577 1.0000 11.750 1.1766 0.02933 0.02353 -0.0077 0.3337 1.0000 12.000 1.1717 0.03134 0.02541 -0.0055 0.3106 1.0000 12.500 1.1640 0.03549 0.02934 -0.0019 0.2692 1.0000 12.750 1.1616 0.03762 0.03137 -0.0004 0.2499 1.0000 13.000 1.1603 0.03974 0.03340 0.0009 0.2324 1.0000 13.250 1.1593 0.04190 0.03548 0.0021 0.2158 1.0000 13.500 1.1599 0.04401 0.03751 0.0031 0.2006 1.0000 13.750 1.1608 0.04616 0.03961 0.0040 0.1864 1.0000 14.000 1.1629 0.04825 0.04166 0.0048 0.1735 1.0000 14.250 1.1649 0.05041 0.04376 0.0055 0.1618 1.0000 14.500 1.1667 0.05259 0.04585 0.0062 0.1514 1.0000 14.750 1.1708 0.05469 0.04797 0.0066 0.1413 1.0000 15.000 1.1753 0.05672 0.05001 0.0071 0.1325 1.0000 15.250 1.1789 0.05882 0.05199 0.0076 0.1247 1.0000 15.500 1.1848 0.06088 0.05417 0.0078 0.1175 1.0000 15.750 1.1902 0.06282 0.05599 0.0082 0.1112 1.0000 16.000 1.1960 0.06498 0.05829 0.0083 0.1053 1.0000 16.250 1.2011 0.06705 0.06029 0.0084 0.0998 1.0000 16.500 1.2065 0.06926 0.06260 0.0085 0.0948 1.0000 16.750 1.2103 0.07167 0.06505 0.0083 0.0900 1.0000 17.000 1.2162 0.07375 0.06713 0.0084 0.0856 1.0000 17.250 1.2198 0.07631 0.06981 0.0081 0.0814 1.0000 17.500 1.2239 0.07870 0.07218 0.0078 0.0777 1.0000 17.750 1.2291 0.08100 0.07455 0.0077 0.0741 1.0000 18.000 1.2311 0.08384 0.07751 0.0071 0.0706 1.0000 18.250 1.2350 0.08634 0.08000 0.0067 0.0676 1.0000 18.500 1.2391 0.08884 0.08260 0.0063 0.0645 1.0000 18.750 1.2400 0.09195 0.08583 0.0056 0.0616 1.0000 19.000 1.2423 0.09478 0.08869 0.0048 0.0590 1.0000 19.250 1.2460 0.09733 0.09127 0.0043 0.0561 1.0000