XFOIL Version 6.96 Calculated polar for: WORTMANN FX 75-141 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 ------ -------- --------- --------- -------- -------- -------- -13.250 -0.4940 0.07288 0.06995 -0.0946 0.8932 0.0200 -13.000 -0.5382 0.05749 0.05427 -0.1096 0.8855 0.0194 -12.750 -0.5634 0.04781 0.04421 -0.1206 0.8781 0.0193 -12.500 -0.5781 0.04146 0.03753 -0.1273 0.8723 0.0191 -12.250 -0.5824 0.03739 0.03317 -0.1313 0.8672 0.0194 -12.000 -0.5842 0.03388 0.02933 -0.1343 0.8627 0.0198 -11.750 -0.5796 0.03127 0.02644 -0.1362 0.8588 0.0199 -11.500 -0.5770 0.02934 0.02429 -0.1362 0.8552 0.0201 -11.250 -0.5767 0.02722 0.02192 -0.1350 0.8514 0.0203 -11.000 -0.5674 0.02518 0.01973 -0.1344 0.8486 0.0208 -10.750 -0.5512 0.02414 0.01861 -0.1340 0.8462 0.0213 -10.500 -0.5329 0.02331 0.01770 -0.1337 0.8441 0.0218 -10.250 -0.5147 0.02254 0.01683 -0.1332 0.8421 0.0225 -10.000 -0.4966 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0.7786 4.750 1.0149 0.00912 0.00419 -0.1168 0.6007 0.7815 5.000 1.0375 0.00927 0.00432 -0.1157 0.5853 0.7848 5.250 1.0582 0.00950 0.00447 -0.1143 0.5645 0.7885 5.500 1.0789 0.00973 0.00464 -0.1129 0.5447 0.7920 5.750 1.1000 0.00994 0.00482 -0.1117 0.5265 0.7951 6.000 1.1196 0.01017 0.00502 -0.1101 0.5068 0.7983 6.250 1.1374 0.01046 0.00526 -0.1082 0.4846 0.8019 6.500 1.1549 0.01077 0.00552 -0.1063 0.4605 0.8057 6.750 1.1694 0.01117 0.00582 -0.1038 0.4320 0.8094 7.000 1.1795 0.01164 0.00617 -0.1006 0.3966 0.8132 7.250 1.1819 0.01223 0.00659 -0.0959 0.3575 0.8179 7.500 1.1838 0.01296 0.00712 -0.0913 0.3166 0.8233 7.750 1.1845 0.01377 0.00776 -0.0867 0.2797 0.8284 8.000 1.1874 0.01457 0.00843 -0.0827 0.2473 0.8337 8.250 1.1918 0.01540 0.00913 -0.0791 0.2196 0.8389 8.500 1.1980 0.01620 0.00985 -0.0760 0.1962 0.8443 8.750 1.2044 0.01704 0.01063 -0.0731 0.1756 0.8508 9.000 1.2118 0.01793 0.01146 -0.0705 0.1566 0.8578 9.250 1.2212 0.01884 0.01233 -0.0684 0.1364 0.8668 9.500 1.2302 0.01991 0.01333 -0.0666 0.1147 0.8802 9.750 1.2445 0.02113 0.01450 -0.0661 0.0909 0.9074 10.000 1.2635 0.02244 0.01577 -0.0668 0.0733 1.0000 10.250 1.2731 0.02370 0.01698 -0.0653 0.0637 1.0000 10.500 1.2829 0.02495 0.01820 -0.0638 0.0569 1.0000 10.750 1.2940 0.02613 0.01940 -0.0625 0.0523 1.0000 11.000 1.3042 0.02736 0.02063 -0.0612 0.0485 1.0000 11.250 1.3116 0.02883 0.02210 -0.0596 0.0449 1.0000 11.500 1.3237 0.02996 0.02329 -0.0586 0.0423 1.0000 11.750 1.3325 0.03134 0.02469 -0.0573 0.0400 1.0000 12.000 1.3354 0.03321 0.02658 -0.0556 0.0374 1.0000 12.250 1.3473 0.03440 0.02784 -0.0546 0.0361 1.0000 12.500 1.3564 0.03583 0.02933 -0.0535 0.0344 1.0000 12.750 1.3639 0.03740 0.03093 -0.0523 0.0327 1.0000 13.000 1.3662 0.03948 0.03304 -0.0509 0.0314 1.0000 13.250 1.3707 0.04143 0.03508 -0.0498 0.0302 1.0000 13.500 1.3791 0.04307 0.03680 -0.0489 0.0292 1.0000 13.750 1.3870 0.04479 0.03858 -0.0482 0.0280 1.0000 14.000 1.3934 0.04671 0.04055 -0.0474 0.0269 1.0000 14.250 1.3953 0.04911 0.04298 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