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 = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -0.9257 0.08876 0.08422 -0.0908 1.0000 0.0525 -19.500 -0.9314 0.08493 0.08034 -0.0926 1.0000 0.0530 -19.250 -0.9378 0.08112 0.07646 -0.0942 1.0000 0.0535 -19.000 -0.9460 0.07712 0.07239 -0.0959 1.0000 0.0540 -18.750 -0.9550 0.07315 0.06833 -0.0975 1.0000 0.0545 -18.500 -0.9644 0.06929 0.06436 -0.0989 1.0000 0.0550 -18.250 -0.9744 0.06547 0.06044 -0.1001 1.0000 0.0554 -18.000 -0.9779 0.06303 0.05803 -0.1000 1.0000 0.0560 -17.750 -0.9860 0.06003 0.05502 -0.1003 1.0000 0.0566 -17.500 -0.9969 0.05682 0.05176 -0.1005 1.0000 0.0570 -17.250 -1.0092 0.05366 0.04855 -0.1005 1.0000 0.0575 -17.000 -1.0224 0.05062 0.04546 -0.1001 1.0000 0.0580 -16.750 -1.0365 0.04771 0.04248 -0.0994 1.0000 0.0585 -16.500 -1.0515 0.04495 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-0.0953 0.6390 0.3054 -2.000 0.2551 0.01058 0.00369 -0.0947 0.6298 0.3158 -1.750 0.2814 0.01056 0.00368 -0.0943 0.6212 0.3265 -1.500 0.3068 0.01052 0.00366 -0.0938 0.6122 0.3400 -1.250 0.3324 0.01051 0.00366 -0.0933 0.6039 0.3556 -1.000 0.3582 0.01047 0.00367 -0.0928 0.5955 0.3744 -0.750 0.3835 0.01048 0.00368 -0.0922 0.5877 0.3958 -0.500 0.4093 0.01043 0.00371 -0.0918 0.5806 0.4194 -0.250 0.4346 0.01040 0.00374 -0.0912 0.5730 0.4451 0.000 0.4595 0.01042 0.00379 -0.0906 0.5655 0.4733 0.250 0.4847 0.01034 0.00384 -0.0900 0.5583 0.5043 0.500 0.5093 0.01033 0.00389 -0.0893 0.5506 0.5373 0.750 0.5335 0.01033 0.00398 -0.0886 0.5433 0.5732 1.000 0.5585 0.01028 0.00407 -0.0879 0.5371 0.6125 1.250 0.5830 0.01027 0.00416 -0.0872 0.5307 0.6500 1.500 0.6077 0.01036 0.00427 -0.0865 0.5244 0.6813 1.750 0.6328 0.01036 0.00438 -0.0858 0.5191 0.7102 2.000 0.6574 0.01037 0.00449 -0.0850 0.5132 0.7388 2.250 0.6814 0.01043 0.00460 -0.0842 0.5076 0.7668 2.500 0.7058 0.01053 0.00475 -0.0834 0.5021 0.7951 2.750 0.7294 0.01055 0.00489 -0.0823 0.4970 0.8250 3.000 0.7523 0.01061 0.00503 -0.0811 0.4916 0.8559 3.250 0.7740 0.01074 0.00520 -0.0796 0.4864 0.8875 3.500 0.7966 0.01091 0.00539 -0.0783 0.4813 0.9182 3.750 0.8208 0.01102 0.00556 -0.0773 0.4764 0.9445 4.000 0.8516 0.01121 0.00574 -0.0779 0.4708 0.9635 4.250 0.8863 0.01148 0.00595 -0.0794 0.4653 0.9778 4.500 0.9265 0.01173 0.00618 -0.0821 0.4598 0.9872 4.750 0.9686 0.01194 0.00640 -0.0853 0.4539 0.9938 5.000 1.0126 0.01222 0.00663 -0.0889 0.4479 0.9995 5.250 1.0213 0.01237 0.00671 -0.0853 0.4428 1.0000 5.500 1.0293 0.01240 0.00677 -0.0815 0.4386 1.0000 5.750 1.0421 0.01251 0.00688 -0.0786 0.4330 1.0000 6.000 1.0571 0.01271 0.00703 -0.0763 0.4269 1.0000 6.250 1.0745 0.01294 0.00723 -0.0745 0.4206 1.0000 6.500 1.0927 0.01313 0.00743 -0.0728 0.4135 1.0000 6.750 1.1097 0.01343 0.00767 -0.0710 0.4063 1.0000 7.000 1.1294 0.01368 0.00793 -0.0698 0.3998 1.0000 7.250 1.1490 0.01396 0.00820 -0.0685 0.3931 1.0000 7.500 1.1665 0.01434 0.00853 -0.0670 0.3865 1.0000 7.750 1.1870 0.01463 0.00884 -0.0659 0.3802 1.0000 8.000 1.2059 0.01498 0.00919 -0.0647 0.3732 1.0000 8.250 1.2227 0.01544 0.00961 -0.0632 0.3663 1.0000 8.500 1.2425 0.01580 0.00999 -0.0622 0.3589 1.0000 8.750 1.2586 0.01632 0.01046 -0.0607 0.3512 1.0000 9.000 1.2769 0.01677 0.01093 -0.0595 0.3439 1.0000 9.250 1.2933 0.01732 0.01146 -0.0581 0.3360 1.0000 9.500 1.3093 0.01791 0.01204 -0.0568 0.3285 1.0000 9.750 1.3252 0.01853 0.01265 -0.0554 0.3202 1.0000 10.000 1.3393 0.01925 0.01334 -0.0539 0.3124 1.0000 10.250 1.3546 0.01994 0.01403 -0.0527 0.3043 1.0000 10.500 1.3668 0.02081 0.01487 -0.0511 0.2968 1.0000 10.750 1.3821 0.02155 0.01563 -0.0499 0.2894 1.0000 11.000 1.3923 0.02258 0.01661 -0.0482 0.2819 1.0000 11.250 1.4068 0.02341 0.01747 -0.0471 0.2750 1.0000 11.500 1.4165 0.02454 0.01857 -0.0455 0.2672 1.0000 11.750 1.4285 0.02558 0.01962 -0.0443 0.2601 1.0000 12.000 1.4380 0.02679 0.02082 -0.0429 0.2524 1.0000 12.250 1.4477 0.02804 0.02208 -0.0416 0.2454 1.0000 12.500 1.4568 0.02937 0.02341 -0.0403 0.2376 1.0000 12.750 1.4647 0.03084 0.02487 -0.0391 0.2304 1.0000 13.000 1.4723 0.03237 0.02641 -0.0379 0.2223 1.0000 13.250 1.4785 0.03404 0.02808 -0.0367 0.2146 1.0000 13.500 1.4828 0.03592 0.02995 -0.0355 0.2062 1.0000 13.750 1.4874 0.03784 0.03188 -0.0345 0.1977 1.0000 14.000 1.4868 0.04025 0.03426 -0.0333 0.1892 1.0000 14.250 1.4909 0.04231 0.03633 -0.0324 0.1808 1.0000 14.500 1.4905 0.04482 0.03884 -0.0314 0.1734 1.0000 14.750 1.4899 0.04742 0.04145 -0.0306 0.1663 1.0000 15.000 1.4900 0.05000 0.04403 -0.0299 0.1600 1.0000 15.250 1.4880 0.05282 0.04686 -0.0292 0.1540 1.0000 15.500 1.4865 0.05565 0.04971 -0.0286 0.1491 1.0000 15.750 1.4856 0.05847 0.05257 -0.0282 0.1443 1.0000 16.000 1.4803 0.06178 0.05588 -0.0277 0.1401 1.0000 16.250 1.4824 0.06434 0.05850 -0.0275 0.1364 1.0000 16.500 1.4802 0.06738 0.06157 -0.0272 0.1328 1.0000 16.750 1.4746 0.07083 0.06502 -0.0270 0.1295 1.0000 17.000 1.4769 0.07347 0.06773 -0.0270 0.1267 1.0000 17.250 1.4772 0.07632 0.07063 -0.0270 0.1237 1.0000 17.500 1.4727 0.07973 0.07406 -0.0271 0.1211 1.0000 17.750 1.4704 0.08289 0.07724 -0.0271 0.1186 1.0000 18.000 1.4725 0.08563 0.08006 -0.0274 0.1163 1.0000 18.250 1.4731 0.08852 0.08300 -0.0276 0.1139 1.0000 18.500 1.4701 0.09188 0.08639 -0.0280 0.1116 1.0000