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 = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -18.250 -0.7301 0.10127 0.09565 -0.0816 1.0000 0.0596 -18.000 -0.7666 0.09250 0.08666 -0.0860 1.0000 0.0605 -17.750 -0.7747 0.08861 0.08275 -0.0874 1.0000 0.0612 -17.500 -0.7839 0.08467 0.07879 -0.0888 1.0000 0.0619 -17.250 -0.7979 0.08009 0.07416 -0.0904 1.0000 0.0627 -17.000 -0.8146 0.07533 0.06932 -0.0921 1.0000 0.0635 -16.750 -0.8326 0.07065 0.06455 -0.0936 1.0000 0.0642 -16.500 -0.8509 0.06620 0.06000 -0.0947 1.0000 0.0650 -16.250 -0.8689 0.06210 0.05578 -0.0954 1.0000 0.0658 -16.000 -0.8853 0.05847 0.05208 -0.0956 1.0000 0.0665 -15.750 -0.9011 0.05521 0.04879 -0.0954 1.0000 0.0671 -15.500 -0.9181 0.05206 0.04560 -0.0948 1.0000 0.0677 -15.250 -0.9356 0.04915 0.04263 -0.0938 1.0000 0.0683 -15.000 -0.9332 0.04588 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0.6002 0.3786 -0.750 0.3614 0.01431 0.00563 -0.0883 0.5927 0.3990 -0.250 0.4114 0.01427 0.00570 -0.0871 0.5788 0.4458 0.000 0.4359 0.01424 0.00575 -0.0864 0.5715 0.4726 0.500 0.4851 0.01421 0.00589 -0.0850 0.5587 0.5312 0.750 0.5095 0.01422 0.00599 -0.0843 0.5521 0.5611 1.000 0.5341 0.01425 0.00607 -0.0835 0.5460 0.5924 1.250 0.5580 0.01427 0.00621 -0.0827 0.5396 0.6243 1.500 0.5817 0.01432 0.00634 -0.0818 0.5327 0.6544 1.750 0.6057 0.01439 0.00644 -0.0809 0.5260 0.6832 2.000 0.6291 0.01445 0.00658 -0.0799 0.5198 0.7122 2.250 0.6520 0.01452 0.00675 -0.0787 0.5132 0.7417 2.500 0.6751 0.01461 0.00690 -0.0776 0.5074 0.7715 2.750 0.6989 0.01474 0.00706 -0.0766 0.5022 0.8012 3.000 0.7217 0.01485 0.00728 -0.0754 0.4963 0.8315 3.250 0.7459 0.01500 0.00749 -0.0744 0.4905 0.8617 3.500 0.7730 0.01521 0.00769 -0.0741 0.4851 0.8924 3.750 0.8027 0.01543 0.00792 -0.0744 0.4797 0.9217 4.000 0.8364 0.01566 0.00819 -0.0756 0.4736 0.9479 4.250 0.8728 0.01593 0.00843 -0.0775 0.4675 0.9698 4.500 0.9115 0.01624 0.00866 -0.0800 0.4621 0.9863 4.750 0.9524 0.01652 0.00898 -0.0830 0.4557 0.9996 5.000 0.9631 0.01666 0.00909 -0.0799 0.4504 1.0000 5.250 0.9744 0.01682 0.00919 -0.0768 0.4454 1.0000 5.500 0.9885 0.01702 0.00936 -0.0743 0.4406 1.0000 5.750 1.0029 0.01722 0.00959 -0.0720 0.4351 1.0000 6.000 1.0187 0.01747 0.00981 -0.0699 0.4295 1.0000 6.250 1.0364 0.01775 0.01002 -0.0682 0.4243 1.0000 6.500 1.0535 0.01803 0.01034 -0.0665 0.4188 1.0000 6.750 1.0706 0.01834 0.01066 -0.0648 0.4128 1.0000 7.000 1.0879 0.01868 0.01096 -0.0632 0.4070 1.0000 7.250 1.1049 0.01904 0.01131 -0.0616 0.4008 1.0000 7.500 1.1201 0.01944 0.01173 -0.0597 0.3930 1.0000 7.750 1.1341 0.01990 0.01211 -0.0578 0.3850 1.0000 8.000 1.1479 0.02038 0.01264 -0.0559 0.3757 1.0000 8.250 1.1612 0.02093 0.01313 -0.0539 0.3676 1.0000 8.500 1.1766 0.02146 0.01370 -0.0524 0.3597 1.0000 8.750 1.1906 0.02206 0.01428 -0.0507 0.3524 1.0000 9.000 1.2052 0.02268 0.01491 -0.0492 0.3453 1.0000 9.250 1.2188 0.02337 0.01560 -0.0476 0.3374 1.0000 9.500 1.2314 0.02412 0.01633 -0.0460 0.3304 1.0000 9.750 1.2448 0.02488 0.01713 -0.0445 0.3225 1.0000 10.000 1.2556 0.02578 0.01799 -0.0428 0.3152 1.0000 10.250 1.2683 0.02664 0.01890 -0.0415 0.3076 1.0000 10.500 1.2782 0.02767 0.01990 -0.0399 0.3002 1.0000 10.750 1.2891 0.02869 0.02094 -0.0385 0.2930 1.0000 11.000 1.2982 0.02984 0.02209 -0.0370 0.2854 1.0000 11.250 1.3071 0.03105 0.02330 -0.0355 0.2787 1.0000 11.500 1.3163 0.03229 0.02457 -0.0342 0.2716 1.0000 11.750 1.3225 0.03375 0.02600 -0.0328 0.2651 1.0000 12.000 1.3319 0.03509 0.02740 -0.0317 0.2582 1.0000 12.250 1.3376 0.03671 0.02902 -0.0304 0.2513 1.0000 12.500 1.3448 0.03828 0.03061 -0.0293 0.2448 1.0000 12.750 1.3505 0.04001 0.03238 -0.0283 0.2379 1.0000 13.000 1.3547 0.04190 0.03427 -0.0272 0.2318 1.0000 13.250 1.3609 0.04371 0.03614 -0.0264 0.2248 1.0000 13.500 1.3624 0.04595 0.03837 -0.0254 0.2184 1.0000 13.750 1.3674 0.04796 0.04045 -0.0248 0.2115 1.0000 14.000 1.3683 0.05038 0.04287 -0.0240 0.2049 1.0000 14.250 1.3712 0.05269 0.04523 -0.0235 0.1984 1.0000 14.500 1.3709 0.05534 0.04791 -0.0229 0.1918 1.0000 14.750 1.3719 0.05794 0.05054 -0.0225 0.1853 1.0000 15.000 1.3699 0.06088 0.05350 -0.0222 0.1786 1.0000 15.250 1.3686 0.06381 0.05645 -0.0219 0.1721 1.0000 15.500 1.3653 0.06701 0.05967 -0.0218 0.1656 1.0000 15.750 1.3632 0.07013 0.06282 -0.0217 0.1594 1.0000 16.000 1.3589 0.07355 0.06625 -0.0217 0.1535 1.0000 16.250 1.3567 0.07674 0.06947 -0.0218 0.1481 1.0000 16.500 1.3538 0.08007 0.07283 -0.0220 0.1431 1.0000 16.750 1.3510 0.08339 0.07617 -0.0222 0.1392 1.0000 17.000 1.3516 0.08636 0.07920 -0.0225 0.1353 1.0000 17.250 1.3497 0.08963 0.08250 -0.0229 0.1319 1.0000 17.500 1.3485 0.09279 0.08567 -0.0233 0.1288 1.0000