XFOIL Version 6.96 Calculated polar for: NACA 16-021 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -0.9810 0.10059 0.09479 -0.0834 0.9963 0.0298 -19.500 -0.9889 0.09601 0.09006 -0.0853 0.9956 0.0301 -19.250 -0.9897 0.09256 0.08655 -0.0868 0.9949 0.0305 -19.000 -0.9909 0.08908 0.08298 -0.0883 0.9942 0.0309 -18.750 -0.9920 0.08562 0.07941 -0.0897 0.9936 0.0314 -18.500 -0.9943 0.08222 0.07589 -0.0905 0.9925 0.0318 -18.250 -0.9963 0.07893 0.07247 -0.0911 0.9912 0.0323 -18.000 -0.9976 0.07580 0.06918 -0.0915 0.9899 0.0329 -17.750 -0.9982 0.07286 0.06606 -0.0918 0.9888 0.0334 -17.500 -0.9978 0.07009 0.06310 -0.0919 0.9877 0.0340 -17.250 -0.9963 0.06746 0.06026 -0.0919 0.9866 0.0347 -17.000 -0.9917 0.06520 0.05788 -0.0919 0.9857 0.0353 -16.750 -0.9847 0.06324 0.05587 -0.0920 0.9849 0.0359 -16.500 -0.9768 0.06132 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0.02096 -0.0086 0.8566 0.8097 -1.250 -0.1327 0.02764 0.02087 0.0009 0.8468 0.8230 -1.000 -0.1011 0.02787 0.02109 -0.0003 0.8444 0.8241 -0.750 -0.0674 0.02797 0.02117 -0.0019 0.8427 0.8253 -0.500 -0.0335 0.02801 0.02120 -0.0036 0.8413 0.8267 -0.250 -0.0007 0.02799 0.02117 -0.0051 0.8402 0.8286 0.000 0.0292 0.02781 0.02099 -0.0060 0.8391 0.8314 0.500 0.0334 0.02801 0.02120 0.0036 0.8267 0.8413 0.750 0.0675 0.02797 0.02117 0.0019 0.8253 0.8427 1.000 0.1011 0.02787 0.02109 0.0003 0.8241 0.8444 1.250 0.1326 0.02764 0.02087 -0.0009 0.8230 0.8468 1.750 0.1375 0.02770 0.02096 0.0086 0.8097 0.8566 2.000 0.1738 0.02753 0.02082 0.0065 0.8083 0.8577 2.250 0.2098 0.02728 0.02060 0.0045 0.8072 0.8589 2.500 0.2456 0.02696 0.02032 0.0025 0.8063 0.8604 3.000 0.2467 0.02682 0.02022 0.0130 0.7919 0.8712 3.250 0.2729 0.02684 0.02030 0.0130 0.7870 0.8724 3.750 0.3429 0.02561 0.01916 0.0103 0.7756 0.8749 4.000 0.3108 0.02531 0.01884 0.0226 0.7628 0.8851 4.250 0.3458 0.02465 0.01821 0.0214 0.7526 0.8858 4.500 0.3814 0.02413 0.01774 0.0199 0.7426 0.8866 4.750 0.4031 0.02424 0.01790 0.0208 0.7290 0.8880 5.000 0.4305 0.02408 0.01778 0.0208 0.7158 0.8895 5.250 0.4598 0.02374 0.01748 0.0204 0.7007 0.8911 5.500 0.4935 0.02320 0.01694 0.0193 0.6800 0.8926 5.750 0.5504 0.02214 0.01572 0.0138 0.6334 0.8926 6.000 0.5790 0.02198 0.01501 0.0138 0.5398 0.8942 6.250 0.5582 0.02227 0.01504 0.0236 0.4940 0.9016 6.500 0.5557 0.02337 0.01575 0.0289 0.4212 0.9035 6.750 0.5517 0.02443 0.01649 0.0344 0.3596 0.9062 7.000 0.5472 0.02525 0.01707 0.0399 0.3111 0.9103 7.250 0.5343 0.02564 0.01732 0.0475 0.2809 0.9167 7.500 0.5453 0.02656 0.01802 0.0496 0.2369 0.9180 7.750 0.5582 0.02735 0.01864 0.0514 0.2033 0.9196 8.000 0.5714 0.02802 0.01921 0.0531 0.1769 0.9216 8.250 0.5831 0.02863 0.01974 0.0553 0.1572 0.9243 8.500 0.5743 0.02878 0.01986 0.0621 0.1474 0.9310 8.750 0.5937 0.02945 0.02048 0.0625 0.1307 0.9319 9.000 0.6126 0.03011 0.02110 0.0629 0.1168 0.9330 9.250 0.6307 0.03076 0.02171 0.0636 0.1051 0.9344 9.500 0.6475 0.03146 0.02238 0.0645 0.0954 0.9361 9.750 0.6633 0.03207 0.02300 0.0656 0.0877 0.9383 10.000 0.6686 0.03258 0.02351 0.0690 0.0825 0.9423 10.250 0.6741 0.03302 0.02397 0.0724 0.0778 0.9457 10.500 0.6918 0.03384 0.02478 0.0728 0.0727 0.9467 10.750 0.7113 0.03456 0.02556 0.0730 0.0682 0.9478 11.000 0.7284 0.03540 0.02640 0.0734 0.0645 0.9491 11.250 0.7442 0.03623 0.02727 0.0742 0.0617 0.9508 11.500 0.7580 0.03699 0.02810 0.0754 0.0592 0.9528 11.750 0.7651 0.03769 0.02884 0.0780 0.0574 0.9560 12.000 0.7695 0.03843 0.02959 0.0811 0.0559 0.9592 12.250 0.7860 0.03948 0.03066 0.0813 0.0541 0.9600 12.500 0.8039 0.04040 0.03169 0.0814 0.0523 0.9611 12.750 0.8205 0.04137 0.03273 0.0816 0.0506 0.9622 13.000 0.8350 0.04239 0.03379 0.0821 0.0492 0.9636 13.250 0.8468 0.04347 0.03490 0.0831 0.0481 0.9652 13.500 0.8564 0.04460 0.03604 0.0844 0.0471 0.9671 13.750 0.8631 0.04550 0.03705 0.0868 0.0462 0.9701 14.000 0.8748 0.04655 0.03820 0.0878 0.0451 0.9718 14.250 0.8904 0.04775 0.03948 0.0877 0.0439 0.9727 14.500 0.9047 0.04901 0.04082 0.0877 0.0429 0.9736 14.750 0.9176 0.05032 0.04219 0.0879 0.0420 0.9746 15.000 0.9287 0.05170 0.04361 0.0883 0.0412 0.9757 15.250 0.9394 0.05311 0.04508 0.0889 0.0404 0.9770 15.500 0.9490 0.05453 0.04666 0.0895 0.0395 0.9784 15.750 0.9567 0.05604 0.04830 0.0905 0.0387 0.9802 16.000 0.9614 0.05761 0.04997 0.0919 0.0380 0.9826 16.250 0.9708 0.05938 0.05185 0.0919 0.0372 0.9835 16.500 0.9799 0.06122 0.05379 0.0916 0.0365 0.9842 16.750 0.9878 0.06314 0.05576 0.0915 0.0358 0.9851 17.000 0.9948 0.06510 0.05777 0.0914 0.0352 0.9859 17.250 0.9993 0.06736 0.06017 0.0914 0.0346 0.9869 17.500 1.0009 0.06998 0.06300 0.0914 0.0340 0.9880 17.750 1.0012 0.07276 0.06596 0.0913 0.0334 0.9891 18.000 1.0007 0.07570 0.06908 0.0911 0.0328 0.9903 18.250 0.9995 0.07883 0.07236 0.0907 0.0323 0.9916 18.500 0.9976 0.08210 0.07577 0.0901 0.0318 0.9929 18.750 0.9960 0.08548 0.07927 0.0891 0.0313 0.9938 19.000 0.9951 0.08892 0.08281 0.0877 0.0309 0.9944 19.250 0.9941 0.09237 0.08634 0.0863 0.0305 0.9951