XFOIL Version 6.94 Calculated polar for: WORTMANN FX 05-191 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 ------- -------- --------- --------- -------- ------- ------- 0.500 0.4376 0.01471 0.00912 -0.0941 0.7454 0.7430 1.000 0.4807 0.01471 0.00915 -0.0921 0.7334 0.7528 1.500 0.5402 0.01461 0.00902 -0.0924 0.7256 0.7584 2.000 0.5919 0.01459 0.00899 -0.0926 0.7138 0.7706 2.500 0.6464 0.01449 0.00889 -0.0920 0.7049 0.7750 3.000 0.6865 0.01466 0.00913 -0.0890 0.6925 0.7825 3.500 0.7567 0.01455 0.00894 -0.0926 0.6832 0.7921 4.000 0.7896 0.01475 0.00925 -0.0881 0.6706 0.7977 4.500 0.8498 0.01486 0.00932 -0.0893 0.6594 0.8052 5.000 0.8942 0.01491 0.00943 -0.0878 0.6446 0.8137 5.500 0.9314 0.01511 0.00969 -0.0843 0.6303 0.8199 6.000 0.9883 0.01530 0.00987 -0.0852 0.6155 0.8282 6.500 1.0181 0.01528 0.00984 -0.0804 0.5951 0.8351 7.000 1.0325 0.01545 0.01016 -0.0729 0.5780 0.8436 7.500 1.0604 0.01579 0.01056 -0.0686 0.5575 0.8515 8.000 1.0752 0.01623 0.01105 -0.0618 0.5341 0.8588 8.500 1.0963 0.01701 0.01184 -0.0571 0.5053 0.8663 9.000 1.1074 0.01798 0.01287 -0.0509 0.4735 0.8727 9.500 1.1145 0.01946 0.01429 -0.0446 0.4289 0.8791 10.000 1.1045 0.02230 0.01678 -0.0374 0.3511 0.8857 10.500 1.0764 0.02639 0.02039 -0.0288 0.2593 0.8908 11.000 1.0498 0.03127 0.02477 -0.0217 0.1708 0.8967 11.500 1.0439 0.03578 0.02898 -0.0181 0.1148 0.9010 12.000 1.0528 0.03975 0.03285 -0.0164 0.0912 0.9050 12.500 1.0580 0.04365 0.03674 -0.0140 0.0772 0.9093 13.000 1.0710 0.04737 0.04053 -0.0129 0.0643 0.9132 13.500 1.0841 0.05143 0.04462 -0.0122 0.0548 0.9174 14.000 1.1003 0.05547 0.04871 -0.0122 0.0478 0.9216 14.500 1.1165 0.05936 0.05271 -0.0121 0.0429 0.9255 15.000 1.1313 0.06351 0.05701 -0.0121 0.0394 0.9298 15.500 1.1432 0.06826 0.06182 -0.0125 0.0371 0.9340 16.000 1.1614 0.07259 0.06633 -0.0133 0.0349 0.9385 16.500 1.1722 0.07707 0.07094 -0.0134 0.0333 0.9456 17.000 1.1845 0.08157 0.07560 -0.0137 0.0316 0.9539 17.500 1.1974 0.08614 0.08037 -0.0146 0.0301 0.9716 18.000 1.2130 0.09144 0.08575 -0.0172 0.0286 1.0000 18.500 1.2288 0.09707 0.09161 -0.0199 0.0272 1.0000 19.000 1.2426 0.10306 0.09782 -0.0230 0.0260 1.0000 19.500 1.2557 0.10913 0.10401 -0.0264 0.0250 1.0000 20.000 1.2690 0.11498 0.11001 -0.0296 0.0241 1.0000 20.500 1.2704 0.12317 0.11855 -0.0344 0.0228 1.0000 21.000 1.2744 0.13088 0.12646 -0.0394 0.0217 1.0000 21.500 1.2809 0.13793 0.13359 -0.0442 0.0206 1.0000 22.000 1.2734 0.14779 0.14384 -0.0509 0.0197 1.0000 22.500 1.2678 0.15729 0.15363 -0.0576 0.0188 1.0000 23.000 1.2660 0.16607 0.16254 -0.0644 0.0178 1.0000 23.500 1.2558 0.17647 0.17318 -0.0722 0.0170 1.0000 24.000 1.2319 0.19009 0.18720 -0.0823 0.0161 1.0000 24.500 1.2014 0.20559 0.20304 -0.0938 0.0155 1.0000