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 = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.4409 0.01013 0.00508 -0.1075 0.7428 0.7224 0.500 0.4936 0.01011 0.00507 -0.1073 0.7308 0.7318 1.000 0.5477 0.01020 0.00514 -0.1069 0.7198 0.7380 1.500 0.6022 0.01026 0.00517 -0.1070 0.7066 0.7472 2.000 0.6531 0.01039 0.00532 -0.1063 0.6936 0.7537 2.500 0.7057 0.01060 0.00547 -0.1057 0.6808 0.7591 3.000 0.7569 0.01081 0.00569 -0.1053 0.6674 0.7672 3.500 0.8085 0.01104 0.00591 -0.1049 0.6552 0.7735 4.500 0.9004 0.01161 0.00651 -0.1016 0.6263 0.7851 5.000 0.9511 0.01189 0.00678 -0.1013 0.6123 0.7922 5.500 0.9903 0.01215 0.00705 -0.0982 0.5965 0.7968 6.000 1.0131 0.01233 0.00730 -0.0920 0.5778 0.8033 6.500 1.0468 0.01273 0.00772 -0.0885 0.5587 0.8106 7.000 1.0693 0.01315 0.00820 -0.0827 0.5375 0.8161 7.500 1.0848 0.01392 0.00892 -0.0761 0.5088 0.8228 8.000 1.0996 0.01506 0.00999 -0.0702 0.4683 0.8296 8.500 1.1080 0.01643 0.01125 -0.0636 0.4234 0.8350 9.000 1.0994 0.01889 0.01340 -0.0552 0.3496 0.8410 9.500 1.0795 0.02259 0.01657 -0.0468 0.2524 0.8465 10.000 1.0697 0.02631 0.01985 -0.0406 0.1697 0.8510 10.500 1.0695 0.02963 0.02290 -0.0358 0.1132 0.8549 11.500 1.0982 0.03544 0.02859 -0.0305 0.0725 0.8629 12.000 1.1179 0.03839 0.03154 -0.0291 0.0607 0.8661 12.500 1.1396 0.04128 0.03446 -0.0281 0.0494 0.8694 13.000 1.1575 0.04445 0.03768 -0.0268 0.0406 0.8724 13.500 1.1744 0.04792 0.04122 -0.0258 0.0354 0.8754 14.000 1.1904 0.05165 0.04504 -0.0250 0.0319 0.8790 14.500 1.2074 0.05553 0.04903 -0.0247 0.0294 0.8821 15.000 1.2230 0.05978 0.05340 -0.0248 0.0271 0.8847 16.000 1.2508 0.06896 0.06284 -0.0256 0.0237 0.8899 16.500 1.2637 0.07372 0.06778 -0.0261 0.0226 0.8929 17.000 1.2755 0.07878 0.07297 -0.0270 0.0211 0.8965 17.500 1.2849 0.08443 0.07878 -0.0283 0.0202 0.8997 18.000 1.2970 0.08993 0.08448 -0.0300 0.0192 0.9026 19.000 1.3145 0.10193 0.09682 -0.0342 0.0169 0.9087 19.500 1.3239 0.10782 0.10294 -0.0364 0.0159 0.9126 20.000 1.3303 0.11437 0.10967 -0.0393 0.0147 0.9167 20.500 1.3373 0.12102 0.11652 -0.0426 0.0133 0.9210 21.000 1.3410 0.12786 0.12356 -0.0459 0.0119 0.9263 21.500 1.3416 0.13499 0.13091 -0.0494 0.0103 0.9341 22.000 1.3335 0.14205 0.13817 -0.0519 0.0087 0.9542 24.000 1.2857 0.18371 0.18065 -0.0812 0.0049 1.0000 25.500 1.1967 0.22893 0.22665 -0.1140 0.0050 1.0000 26.000 1.1593 0.24736 0.24530 -0.1263 0.0052 1.0000 26.500 1.1357 0.26319 0.26123 -0.1366 0.0050 1.0000 27.000 1.1305 0.27384 0.27191 -0.1440 0.0048 1.0000