XFOIL Version 6.96 Calculated polar for: EPPLER 560 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -16.250 -0.6343 0.11137 0.10835 -0.0545 1.0000 0.0198 -16.000 -0.6704 0.10088 0.09766 -0.0601 1.0000 0.0194 -15.750 -0.6869 0.09447 0.09114 -0.0635 1.0000 0.0196 -15.500 -0.6999 0.08890 0.08547 -0.0662 1.0000 0.0196 -15.250 -0.7111 0.08388 0.08035 -0.0686 1.0000 0.0196 -15.000 -0.7207 0.07924 0.07562 -0.0707 1.0000 0.0197 -14.750 -0.7290 0.07504 0.07134 -0.0725 1.0000 0.0198 -14.500 -0.7364 0.07115 0.06737 -0.0740 1.0000 0.0199 -14.250 -0.7437 0.06742 0.06357 -0.0753 1.0000 0.0200 -14.000 -0.7503 0.06405 0.06013 -0.0763 1.0000 0.0200 -13.750 -0.7577 0.06085 0.05686 -0.0770 1.0000 0.0201 -13.500 -0.7656 0.05779 0.05375 -0.0775 1.0000 0.0202 -13.250 -0.7736 0.05500 0.05091 -0.0776 1.0000 0.0202 -13.000 -0.7837 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0.0410 -8.250 -0.3521 0.01283 0.00741 -0.1385 0.9276 0.0636 -8.000 -0.3169 0.01208 0.00674 -0.1404 0.9225 0.0841 -7.750 -0.2761 0.01151 0.00620 -0.1432 0.9193 0.1004 -7.500 -0.2421 0.01108 0.00577 -0.1445 0.9102 0.1136 -7.250 -0.1972 0.01065 0.00534 -0.1481 0.9049 0.1276 -7.000 -0.1547 0.01031 0.00500 -0.1512 0.8957 0.1413 -6.500 -0.0664 0.00979 0.00442 -0.1580 0.8733 0.1684 -6.250 -0.0299 0.00964 0.00421 -0.1598 0.8579 0.1802 -6.000 0.0034 0.00956 0.00403 -0.1608 0.8413 0.1907 -5.750 0.0339 0.00950 0.00389 -0.1612 0.8248 0.2002 -5.500 0.0629 0.00945 0.00375 -0.1613 0.8085 0.2092 -5.250 0.0911 0.00947 0.00366 -0.1612 0.7926 0.2186 -5.000 0.1185 0.00942 0.00357 -0.1611 0.7772 0.2275 -4.750 0.1460 0.00946 0.00348 -0.1608 0.7627 0.2355 -4.500 0.1731 0.00941 0.00340 -0.1605 0.7486 0.2434 -4.250 0.2003 0.00945 0.00332 -0.1602 0.7349 0.2505 -4.000 0.2272 0.00942 0.00324 -0.1599 0.7213 0.2577 -3.750 0.2543 0.00944 0.00319 -0.1596 0.7085 0.2649 -3.500 0.2814 0.00942 0.00312 -0.1593 0.6961 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0.01058 0.00359 -0.1533 0.4972 0.4281 2.000 0.8747 0.01068 0.00369 -0.1530 0.4900 0.4380 2.250 0.9011 0.01079 0.00380 -0.1526 0.4834 0.4480 2.500 0.9279 0.01086 0.00391 -0.1524 0.4766 0.4586 2.750 0.9540 0.01100 0.00403 -0.1520 0.4705 0.4699 3.000 0.9807 0.01108 0.00417 -0.1517 0.4645 0.4826 3.250 1.0070 0.01118 0.00430 -0.1513 0.4581 0.4963 3.500 1.0327 0.01135 0.00446 -0.1509 0.4522 0.5113 3.750 1.0593 0.01141 0.00461 -0.1506 0.4468 0.5291 4.000 1.0853 0.01150 0.00477 -0.1503 0.4409 0.5501 4.250 1.1106 0.01169 0.00497 -0.1498 0.4353 0.5747 4.500 1.1370 0.01172 0.00515 -0.1495 0.4301 0.6044 4.750 1.1625 0.01181 0.00534 -0.1490 0.4247 0.6423 5.000 1.1870 0.01197 0.00559 -0.1484 0.4193 0.6898 5.250 1.2116 0.01197 0.00581 -0.1477 0.4144 0.7523 5.500 1.2311 0.01192 0.00601 -0.1458 0.4094 0.8473 5.750 1.2478 0.01191 0.00611 -0.1433 0.4045 1.0000 6.000 1.2729 0.01212 0.00632 -0.1428 0.3996 1.0000 6.250 1.2977 0.01229 0.00650 -0.1422 0.3943 1.0000 6.500 1.3209 0.01254 0.00671 -0.1414 0.3891 1.0000 6.750 1.3443 0.01278 0.00695 -0.1405 0.3842 1.0000 7.000 1.3674 0.01295 0.00716 -0.1396 0.3790 1.0000 7.250 1.3893 0.01321 0.00739 -0.1386 0.3737 1.0000 7.500 1.4112 0.01350 0.00767 -0.1375 0.3686 1.0000 7.750 1.4333 0.01368 0.00790 -0.1364 0.3632 1.0000 8.000 1.4539 0.01395 0.00816 -0.1352 0.3576 1.0000 8.250 1.4746 0.01426 0.00847 -0.1339 0.3522 1.0000 8.500 1.4960 0.01447 0.00874 -0.1328 0.3466 1.0000 8.750 1.5154 0.01479 0.00905 -0.1313 0.3410 1.0000 9.000 1.5350 0.01511 0.00939 -0.1299 0.3354 1.0000 9.250 1.5552 0.01538 0.00971 -0.1287 0.3294 1.0000 9.500 1.5724 0.01579 0.01009 -0.1269 0.3233 1.0000 9.750 1.5918 0.01609 0.01045 -0.1256 0.3168 1.0000 10.000 1.6085 0.01649 0.01086 -0.1238 0.3096 1.0000 10.250 1.6256 0.01690 0.01130 -0.1221 0.3025 1.0000 10.500 1.6414 0.01736 0.01177 -0.1203 0.2945 1.0000 10.750 1.6567 0.01785 0.01228 -0.1185 0.2858 1.0000 11.000 1.6694 0.01847 0.01289 -0.1163 0.2769 1.0000 11.250 1.6841 0.01904 0.01349 -0.1145 0.2672 1.0000 11.500 1.6952 0.01979 0.01423 -0.1123 0.2578 1.0000 11.750 1.7057 0.02059 0.01504 -0.1101 0.2472 1.0000 12.000 1.7161 0.02145 0.01591 -0.1079 0.2364 1.0000 12.250 1.7236 0.02251 0.01695 -0.1056 0.2253 1.0000 12.500 1.7286 0.02377 0.01818 -0.1031 0.2137 1.0000 12.750 1.7326 0.02516 0.01956 -0.1007 0.2016 1.0000 13.000 1.7359 0.02668 0.02107 -0.0984 0.1893 1.0000 13.250 1.7370 0.02844 0.02281 -0.0961 0.1772 1.0000 13.500 1.7362 0.03045 0.02481 -0.0940 0.1657 1.0000 13.750 1.7329 0.03278 0.02712 -0.0919 0.1540 1.0000 14.000 1.7283 0.03538 0.02971 -0.0901 0.1434 1.0000 14.250 1.7248 0.03803 0.03235 -0.0885 0.1331 1.0000 14.500 1.7207 0.04088 0.03523 -0.0873 0.1241 1.0000 14.750 1.7141 0.04412 0.03848 -0.0862 0.1165 1.0000 15.000 1.7096 0.04731 0.04171 -0.0855 0.1086 1.0000 15.250 1.7026 0.05089 0.04533 -0.0849 0.1022 1.0000 15.500 1.6959 0.05460 0.04908 -0.0846 0.0955 1.0000 15.750 1.6883 0.05855 0.05308 -0.0845 0.0899 1.0000 16.000 1.6804 0.06266 0.05724 -0.0846 0.0843 1.0000 16.250 1.6715 0.06706 0.06169 -0.0849 0.0795 1.0000 16.500 1.6646 0.07130 0.06600 -0.0854 0.0748 1.0000 17.000 1.6473 0.08057 0.07540 -0.0870 0.0663 1.0000 17.250 1.6373 0.08558 0.08046 -0.0880 0.0623 1.0000 17.500 1.6288 0.09047 0.08541 -0.0892 0.0587 1.0000 17.750 1.6212 0.09527 0.09028 -0.0905 0.0551 1.0000