XFOIL Version 6.96 Calculated polar for: NACA 4421 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 ------ -------- --------- --------- -------- -------- -------- -19.750 -0.9805 0.08344 0.07962 -0.0909 1.0000 0.0436 -19.500 -0.9971 0.07828 0.07438 -0.0932 1.0000 0.0439 -19.250 -1.0148 0.07317 0.06918 -0.0954 1.0000 0.0443 -19.000 -1.0341 0.06805 0.06398 -0.0973 1.0000 0.0446 -18.750 -1.0541 0.06308 0.05892 -0.0990 1.0000 0.0449 -18.500 -1.0749 0.05829 0.05403 -0.1003 1.0000 0.0451 -18.250 -1.0967 0.05368 0.04932 -0.1013 1.0000 0.0453 -18.000 -1.1167 0.04961 0.04515 -0.1015 1.0000 0.0455 -17.500 -1.1664 0.04160 0.03695 -0.1005 1.0000 0.0459 -17.250 -1.1777 0.03744 0.03270 -0.1025 0.9992 0.0464 -17.000 -1.1718 0.03398 0.02916 -0.1059 0.9976 0.0470 -16.750 -1.1600 0.03131 0.02642 -0.1088 0.9958 0.0477 -16.500 -1.1439 0.02916 0.02421 -0.1113 0.9943 0.0484 -16.250 -1.1242 0.02741 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-0.0942 0.5799 0.2736 -1.750 0.2804 0.00889 0.00266 -0.0938 0.5715 0.2808 -1.500 0.3068 0.00892 0.00267 -0.0934 0.5636 0.2874 -1.250 0.3340 0.00888 0.00266 -0.0932 0.5568 0.2975 -0.750 0.3864 0.00889 0.00268 -0.0924 0.5415 0.3209 -0.500 0.4130 0.00886 0.00269 -0.0921 0.5339 0.3374 -0.250 0.4378 0.00888 0.00273 -0.0914 0.5253 0.3575 0.000 0.4646 0.00884 0.00276 -0.0912 0.5191 0.3802 0.250 0.4910 0.00882 0.00279 -0.0908 0.5129 0.4026 0.500 0.5162 0.00884 0.00284 -0.0903 0.5063 0.4250 0.750 0.5423 0.00882 0.00289 -0.0899 0.5008 0.4509 1.000 0.5688 0.00878 0.00294 -0.0896 0.4955 0.4814 1.250 0.5943 0.00878 0.00301 -0.0891 0.4898 0.5122 1.500 0.6183 0.00880 0.00309 -0.0883 0.4834 0.5460 1.750 0.6448 0.00874 0.00317 -0.0880 0.4792 0.5859 2.000 0.6706 0.00871 0.00325 -0.0876 0.4742 0.6222 2.250 0.6953 0.00874 0.00335 -0.0869 0.4689 0.6526 2.500 0.7177 0.00882 0.00346 -0.0858 0.4629 0.6807 2.750 0.7433 0.00881 0.00354 -0.0853 0.4591 0.7066 3.000 0.7678 0.00884 0.00363 -0.0846 0.4544 0.7311 3.250 0.7913 0.00890 0.00375 -0.0836 0.4495 0.7562 3.750 0.8394 0.00903 0.00404 -0.0821 0.4399 0.8127 4.000 0.8639 0.00907 0.00419 -0.0813 0.4353 0.8466 4.250 0.8864 0.00916 0.00436 -0.0801 0.4305 0.8831 4.500 0.9060 0.00932 0.00457 -0.0783 0.4252 0.9190 4.750 0.9286 0.00944 0.00474 -0.0771 0.4208 0.9478 5.000 0.9564 0.00958 0.00490 -0.0771 0.4152 0.9703 5.250 0.9882 0.00983 0.00510 -0.0781 0.4080 0.9863 5.750 1.0543 0.01023 0.00545 -0.0808 0.3938 1.0000 6.000 1.0690 0.01047 0.00563 -0.0784 0.3863 1.0000 6.250 1.0909 0.01061 0.00577 -0.0774 0.3807 1.0000 6.500 1.1119 0.01082 0.00595 -0.0763 0.3741 1.0000 6.750 1.1308 0.01112 0.00621 -0.0748 0.3671 1.0000 7.000 1.1541 0.01131 0.00640 -0.0741 0.3614 1.0000 7.250 1.1747 0.01160 0.00666 -0.0731 0.3538 1.0000 7.500 1.1954 0.01191 0.00693 -0.0720 0.3465 1.0000 7.750 1.2165 0.01221 0.00721 -0.0711 0.3388 1.0000 8.000 1.2353 0.01261 0.00757 -0.0698 0.3308 1.0000 8.250 1.2565 0.01293 0.00787 -0.0689 0.3227 1.0000 8.500 1.2740 0.01341 0.00830 -0.0675 0.3137 1.0000 8.750 1.2938 0.01381 0.00868 -0.0665 0.3050 1.0000 9.000 1.3111 0.01433 0.00916 -0.0652 0.2964 1.0000 9.250 1.3298 0.01480 0.00961 -0.0641 0.2887 1.0000 9.500 1.3457 0.01541 0.01017 -0.0626 0.2806 1.0000 9.750 1.3645 0.01590 0.01065 -0.0616 0.2733 1.0000 10.250 1.3966 0.01717 0.01187 -0.0590 0.2579 1.0000 10.500 1.4097 0.01798 0.01264 -0.0574 0.2498 1.0000 10.750 1.4272 0.01858 0.01324 -0.0564 0.2437 1.0000 11.000 1.4413 0.01938 0.01402 -0.0550 0.2365 1.0000 11.250 1.4558 0.02017 0.01480 -0.0538 0.2296 1.0000 11.500 1.4689 0.02106 0.01566 -0.0524 0.2216 1.0000 11.750 1.4814 0.02202 0.01660 -0.0511 0.2140 1.0000 12.000 1.4922 0.02310 0.01766 -0.0496 0.2056 1.0000 12.250 1.5040 0.02416 0.01871 -0.0484 0.1980 1.0000 12.500 1.5118 0.02551 0.02002 -0.0468 0.1890 1.0000 12.750 1.5206 0.02683 0.02131 -0.0454 0.1798 1.0000 13.000 1.5275 0.02833 0.02279 -0.0440 0.1710 1.0000 13.250 1.5327 0.02999 0.02442 -0.0425 0.1625 1.0000 13.500 1.5384 0.03169 0.02610 -0.0412 0.1547 1.0000 13.750 1.5433 0.03347 0.02787 -0.0399 0.1478 1.0000 14.000 1.5464 0.03544 0.02983 -0.0386 0.1412 1.0000 14.250 1.5516 0.03732 0.03172 -0.0376 0.1358 1.0000 14.500 1.5536 0.03952 0.03392 -0.0365 0.1307 1.0000 14.750 1.5590 0.04144 0.03586 -0.0356 0.1267 1.0000 15.000 1.5621 0.04363 0.03807 -0.0348 0.1231 1.0000 15.250 1.5623 0.04612 0.04058 -0.0339 0.1194 1.0000 15.500 1.5683 0.04810 0.04260 -0.0333 0.1169 1.0000 15.750 1.5708 0.05048 0.04501 -0.0328 0.1143 1.0000 16.000 1.5711 0.05307 0.04764 -0.0322 0.1116 1.0000 16.250 1.5711 0.05573 0.05033 -0.0316 0.1091 1.0000 16.500 1.5746 0.05809 0.05275 -0.0313 0.1073 1.0000 16.750 1.5771 0.06054 0.05524 -0.0310 0.1053 1.0000 17.000 1.5758 0.06348 0.05821 -0.0307 0.1032 1.0000 17.250 1.5720 0.06666 0.06144 -0.0304 0.1011 1.0000 17.500 1.5738 0.06925 0.06409 -0.0303 0.0995 1.0000 17.750 1.5750 0.07197 0.06687 -0.0302 0.0978 1.0000 18.000 1.5755 0.07476 0.06970 -0.0302 0.0960 1.0000 18.250 1.5715 0.07812 0.07309 -0.0302 0.0941 1.0000 18.500 1.5665 0.08156 0.07657 -0.0303 0.0921 1.0000 18.750 1.5677 0.08434 0.07942 -0.0304 0.0907 1.0000 19.000 1.5693 0.08705 0.08218 -0.0306 0.0889 1.0000 19.250 1.5657 0.09046 0.08564 -0.0310 0.0872 1.0000