XFOIL Version 6.96 Calculated polar for: WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT N 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -16.250 -0.7108 0.09465 0.09253 -0.0465 0.9998 0.0105 -16.000 -0.7360 0.08538 0.08311 -0.0523 0.9998 0.0105 -15.750 -0.7593 0.07705 0.07462 -0.0575 0.9998 0.0104 -15.500 -0.7801 0.06975 0.06716 -0.0620 0.9998 0.0104 -15.250 -0.8010 0.06296 0.06020 -0.0660 0.9998 0.0105 -15.000 -0.8178 0.05712 0.05378 -0.0698 0.8384 0.0106 -14.750 -0.8313 0.05277 0.04905 -0.0716 0.7767 0.0106 -14.500 -0.8396 0.04899 0.04500 -0.0732 0.7396 0.0107 -14.250 -0.8430 0.04587 0.04168 -0.0745 0.7115 0.0108 -14.000 -0.8430 0.04316 0.03880 -0.0756 0.6892 0.0109 -13.500 -0.8358 0.03864 0.03401 -0.0773 0.6589 0.0112 -13.250 -0.8300 0.03664 0.03188 -0.0781 0.6483 0.0113 -13.000 -0.8229 0.03479 0.02991 -0.0787 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0.0196 0.00819 0.00237 -0.0827 0.5223 0.3906 -3.250 0.0477 0.00798 0.00229 -0.0830 0.5206 0.4412 -3.000 0.0762 0.00788 0.00224 -0.0833 0.5189 0.4720 -2.750 0.1048 0.00784 0.00224 -0.0836 0.5169 0.4966 -2.500 0.1337 0.00787 0.00227 -0.0839 0.5146 0.5179 -2.250 0.1631 0.00785 0.00226 -0.0843 0.5134 0.5303 -2.000 0.1925 0.00785 0.00228 -0.0847 0.5119 0.5438 -1.750 0.2219 0.00787 0.00231 -0.0850 0.5104 0.5568 -1.500 0.2515 0.00792 0.00232 -0.0855 0.5088 0.5643 -1.250 0.2809 0.00792 0.00232 -0.0859 0.5072 0.5695 -1.000 0.3103 0.00796 0.00234 -0.0863 0.5057 0.5752 -0.750 0.3398 0.00802 0.00235 -0.0867 0.5041 0.5805 -0.500 0.3689 0.00806 0.00238 -0.0871 0.5024 0.5858 -0.250 0.3980 0.00816 0.00245 -0.0874 0.5003 0.5908 0.000 0.4274 0.00822 0.00249 -0.0879 0.4988 0.5951 0.250 0.4570 0.00823 0.00250 -0.0883 0.4976 0.5985 0.500 0.4863 0.00824 0.00252 -0.0888 0.4963 0.6022 0.750 0.5156 0.00827 0.00256 -0.0892 0.4949 0.6059 1.000 0.5450 0.00832 0.00260 -0.0896 0.4934 0.6094 1.250 0.5744 0.00837 0.00263 -0.0901 0.4920 0.6125 1.500 0.6036 0.00839 0.00266 -0.0905 0.4905 0.6158 1.750 0.6326 0.00843 0.00270 -0.0909 0.4890 0.6191 2.000 0.6616 0.00851 0.00277 -0.0913 0.4872 0.6224 2.250 0.6905 0.00864 0.00287 -0.0917 0.4851 0.6258 2.500 0.7197 0.00871 0.00295 -0.0922 0.4839 0.6287 2.750 0.7488 0.00872 0.00300 -0.0926 0.4828 0.6319 3.000 0.7779 0.00875 0.00307 -0.0930 0.4816 0.6349 3.250 0.8069 0.00880 0.00314 -0.0934 0.4802 0.6381 3.500 0.8359 0.00886 0.00322 -0.0939 0.4787 0.6413 3.750 0.8649 0.00892 0.00328 -0.0943 0.4771 0.6443 4.000 0.8937 0.00896 0.00335 -0.0947 0.4756 0.6474 4.250 0.9224 0.00902 0.00344 -0.0951 0.4742 0.6505 4.500 0.9510 0.00911 0.00355 -0.0955 0.4727 0.6536 4.750 0.9795 0.00925 0.00369 -0.0958 0.4707 0.6568 5.000 1.0082 0.00937 0.00382 -0.0962 0.4691 0.6600 5.250 1.0368 0.00940 0.00392 -0.0966 0.4680 0.6632 5.500 1.0653 0.00945 0.00403 -0.0970 0.4667 0.6664 5.750 1.0937 0.00951 0.00414 -0.0974 0.4649 0.6698 6.000 1.1221 0.00954 0.00421 -0.0977 0.4625 0.6734 6.250 1.1504 0.00960 0.00429 -0.0980 0.4601 0.6767 6.500 1.1778 0.00968 0.00439 -0.0983 0.4561 0.6804 6.750 1.2057 0.00970 0.00448 -0.0985 0.4525 0.6842 7.000 1.2338 0.00970 0.00454 -0.0988 0.4486 0.6883 7.250 1.2613 0.00975 0.00460 -0.0990 0.4435 0.6923 7.500 1.2882 0.00986 0.00475 -0.0992 0.4395 0.6967 7.750 1.3162 0.00989 0.00487 -0.0995 0.4359 0.7015 8.000 1.3437 0.00996 0.00499 -0.0997 0.4314 0.7064 8.250 1.3697 0.01011 0.00515 -0.0997 0.4255 0.7113 8.500 1.3972 0.01015 0.00529 -0.1000 0.4182 0.7167 8.750 1.4227 0.01032 0.00545 -0.0999 0.4064 0.7225 9.000 1.4459 0.01061 0.00570 -0.0995 0.3860 0.7281 9.250 1.4621 0.01134 0.00626 -0.0981 0.3456 0.7348 9.500 1.4592 0.01318 0.00766 -0.0939 0.2716 0.7419 9.750 1.4389 0.01547 0.00956 -0.0872 0.1998 0.7502 10.000 1.4157 0.01811 0.01195 -0.0813 0.1473 0.7597 10.250 1.3987 0.02108 0.01481 -0.0778 0.1124 0.7711 10.500 1.3815 0.02490 0.01857 -0.0760 0.0821 0.7851 10.750 1.3692 0.02872 0.02241 -0.0750 0.0616 0.8045 11.000 1.3618 0.03193 0.02579 -0.0740 0.0501 0.8591 11.250 1.3561 0.03472 0.02879 -0.0728 0.0431 1.0002 11.500 1.3518 0.03779 0.03188 -0.0721 0.0376 1.0002 11.750 1.3509 0.04049 0.03462 -0.0714 0.0337 1.0002 12.000 1.3468 0.04346 0.03760 -0.0706 0.0298 1.0002 12.250 1.3466 0.04605 0.04023 -0.0699 0.0275 1.0002 12.500 1.3453 0.04880 0.04300 -0.0692 0.0251 1.0002 12.750 1.3444 0.05158 0.04582 -0.0687 0.0231 1.0002 13.000 1.3470 0.05405 0.04834 -0.0683 0.0219 1.0002 13.250 1.3482 0.05672 0.05103 -0.0679 0.0206 1.0002 13.500 1.3485 0.05948 0.05382 -0.0675 0.0192 1.0002 13.750 1.3503 0.06212 0.05650 -0.0672 0.0181 1.0002 14.000 1.3542 0.06454 0.05897 -0.0669 0.0172 1.0002 14.250 1.3560 0.06725 0.06172 -0.0667 0.0163 1.0002 14.500 1.3572 0.06999 0.06449 -0.0664 0.0152 1.0002 14.750 1.3570 0.07295 0.06750 -0.0662 0.0143 1.0002 15.000 1.3622 0.07530 0.06990 -0.0661 0.0136 1.0002 15.250 1.3656 0.07787 0.07251 -0.0660 0.0129 1.0002 15.500 1.3674 0.08065 0.07533 -0.0659 0.0122 1.0002 15.750 1.3668 0.08368 0.07839 -0.0658 0.0113 1.0002 16.000 1.3701 0.08633 0.08110 -0.0658 0.0109 1.0002 16.250 1.3743 0.08886 0.08367 -0.0659 0.0104 1.0002 16.500 1.3787 0.09137 0.08622 -0.0659 0.0098 1.0002 16.750 1.3804 0.09424 0.08913 -0.0661 0.0092 1.0002 17.000 1.3800 0.09737 0.09229 -0.0662 0.0087 1.0002 17.250 1.3834 0.10001 0.09499 -0.0664 0.0083 1.0002 17.500 1.3858 0.10284 0.09787 -0.0666 0.0079 1.0002 17.750 1.3890 0.10555 0.10063 -0.0669 0.0075 1.0002 18.000 1.3913 0.10838 0.10349 -0.0672 0.0071 1.0002 18.250 1.3888 0.11191 0.10706 -0.0677 0.0066 1.0002 18.500 1.3887 0.11508 0.11029 -0.0682 0.0063 1.0002