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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.000 -0.8741 0.08931 0.08468 -0.0868 1.0000 0.0449 -18.750 -0.8866 0.08468 0.07998 -0.0887 1.0000 0.0453 -18.500 -0.8990 0.08024 0.07546 -0.0904 1.0000 0.0457 -18.250 -0.9175 0.07517 0.07033 -0.0922 1.0000 0.0461 -18.000 -0.9381 0.06999 0.06508 -0.0941 1.0000 0.0464 -17.750 -0.9603 0.06488 0.05988 -0.0956 1.0000 0.0467 -17.500 -0.9828 0.06007 0.05499 -0.0967 1.0000 0.0470 -17.250 -1.0059 0.05546 0.05029 -0.0974 1.0000 0.0474 -17.000 -1.0268 0.05118 0.04592 -0.0979 0.9999 0.0477 -16.750 -1.0285 0.04673 0.04136 -0.1017 0.9981 0.0483 -16.500 -1.0259 0.04289 0.03742 -0.1051 0.9960 0.0490 -16.250 -1.0187 0.03957 0.03399 -0.1083 0.9939 0.0497 -16.000 -1.0078 0.03667 0.03098 -0.1115 0.9922 0.0504 -15.750 -1.0016 0.03370 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-0.0895 0.5429 0.2818 -1.000 0.3427 0.01110 0.00350 -0.0892 0.5363 0.2903 -0.750 0.3683 0.01110 0.00351 -0.0887 0.5298 0.3004 -0.250 0.4199 0.01111 0.00356 -0.0878 0.5185 0.3253 0.000 0.4454 0.01109 0.00360 -0.0873 0.5122 0.3433 0.250 0.4696 0.01110 0.00364 -0.0865 0.5054 0.3649 0.500 0.4947 0.01109 0.00369 -0.0860 0.4989 0.3890 0.750 0.5196 0.01108 0.00375 -0.0854 0.4917 0.4136 1.000 0.5435 0.01110 0.00382 -0.0846 0.4853 0.4400 1.250 0.5683 0.01109 0.00390 -0.0840 0.4803 0.4674 1.500 0.5937 0.01108 0.00397 -0.0835 0.4750 0.4920 1.750 0.6181 0.01110 0.00406 -0.0828 0.4695 0.5169 2.000 0.6407 0.01114 0.00416 -0.0818 0.4641 0.5444 2.250 0.6645 0.01115 0.00426 -0.0810 0.4596 0.5738 2.500 0.6885 0.01116 0.00437 -0.0802 0.4548 0.6032 2.750 0.7113 0.01121 0.00449 -0.0792 0.4495 0.6319 3.000 0.7334 0.01131 0.00464 -0.0781 0.4443 0.6587 3.250 0.7578 0.01137 0.00478 -0.0774 0.4400 0.6857 3.500 0.7824 0.01143 0.00494 -0.0768 0.4353 0.7130 3.750 0.8058 0.01153 0.00512 -0.0759 0.4300 0.7401 4.000 0.8280 0.01167 0.00531 -0.0749 0.4248 0.7670 4.250 0.8516 0.01176 0.00550 -0.0740 0.4205 0.7964 4.500 0.8747 0.01185 0.00571 -0.0731 0.4157 0.8297 4.750 0.8951 0.01197 0.00594 -0.0715 0.4104 0.8698 5.000 0.9138 0.01217 0.00620 -0.0696 0.4052 0.9136 5.250 0.9409 0.01235 0.00644 -0.0694 0.4005 0.9533 5.500 0.9745 0.01258 0.00667 -0.0708 0.3947 0.9824 5.750 1.0032 0.01285 0.00690 -0.0714 0.3880 1.0000 6.000 1.0225 0.01309 0.00712 -0.0700 0.3817 1.0000 6.250 1.0418 0.01336 0.00736 -0.0687 0.3735 1.0000 6.500 1.0596 0.01371 0.00766 -0.0671 0.3651 1.0000 6.750 1.0787 0.01404 0.00795 -0.0659 0.3552 1.0000 7.000 1.0964 0.01444 0.00831 -0.0644 0.3463 1.0000 7.250 1.1156 0.01482 0.00866 -0.0632 0.3372 1.0000 7.500 1.1334 0.01526 0.00906 -0.0619 0.3297 1.0000 7.750 1.1525 0.01568 0.00946 -0.0607 0.3212 1.0000 8.000 1.1694 0.01620 0.00994 -0.0593 0.3133 1.0000 8.250 1.1879 0.01667 0.01040 -0.0582 0.3052 1.0000 8.500 1.2036 0.01728 0.01097 -0.0568 0.2969 1.0000 8.750 1.2211 0.01784 0.01150 -0.0556 0.2888 1.0000 9.000 1.2354 0.01855 0.01218 -0.0541 0.2809 1.0000 9.250 1.2530 0.01913 0.01276 -0.0530 0.2742 1.0000 9.500 1.2674 0.01989 0.01350 -0.0516 0.2671 1.0000 9.750 1.2832 0.02060 0.01420 -0.0505 0.2608 1.0000 10.000 1.2976 0.02140 0.01499 -0.0492 0.2538 1.0000 10.250 1.3107 0.02229 0.01586 -0.0478 0.2474 1.0000 10.500 1.3257 0.02310 0.01668 -0.0467 0.2410 1.0000 10.750 1.3378 0.02410 0.01767 -0.0454 0.2346 1.0000 11.000 1.3515 0.02504 0.01861 -0.0443 0.2289 1.0000 11.250 1.3639 0.02608 0.01965 -0.0431 0.2222 1.0000 11.500 1.3741 0.02729 0.02086 -0.0418 0.2157 1.0000 11.750 1.3849 0.02850 0.02206 -0.0406 0.2077 1.0000 12.000 1.3931 0.02994 0.02349 -0.0394 0.2002 1.0000 12.250 1.4010 0.03144 0.02498 -0.0382 0.1918 1.0000 12.500 1.4085 0.03301 0.02655 -0.0370 0.1841 1.0000 12.750 1.4126 0.03490 0.02841 -0.0358 0.1760 1.0000 13.000 1.4189 0.03666 0.03017 -0.0347 0.1679 1.0000 13.250 1.4226 0.03869 0.03219 -0.0337 0.1603 1.0000 13.500 1.4246 0.04092 0.03442 -0.0326 0.1528 1.0000 13.750 1.4280 0.04308 0.03658 -0.0318 0.1462 1.0000 14.000 1.4283 0.04556 0.03906 -0.0309 0.1398 1.0000 14.250 1.4305 0.04794 0.04146 -0.0302 0.1338 1.0000 14.500 1.4299 0.05063 0.04416 -0.0295 0.1289 1.0000 14.750 1.4334 0.05294 0.04650 -0.0290 0.1248 1.0000 15.000 1.4342 0.05557 0.04916 -0.0285 0.1213 1.0000 15.250 1.4347 0.05829 0.05191 -0.0281 0.1184 1.0000 15.500 1.4384 0.06068 0.05436 -0.0279 0.1158 1.0000 15.750 1.4390 0.06345 0.05717 -0.0276 0.1131 1.0000 16.000 1.4384 0.06636 0.06011 -0.0274 0.1106 1.0000 16.250 1.4390 0.06916 0.06296 -0.0273 0.1085 1.0000 16.500 1.4408 0.07187 0.06573 -0.0272 0.1063 1.0000 16.750 1.4413 0.07474 0.06865 -0.0272 0.1040 1.0000 17.000 1.4392 0.07795 0.07190 -0.0273 0.1018 1.0000 17.250 1.4385 0.08098 0.07497 -0.0274 0.0999 1.0000 17.500 1.4396 0.08384 0.07790 -0.0276 0.0980 1.0000 17.750 1.4405 0.08673 0.08084 -0.0279 0.0959 1.0000 18.000 1.4385 0.09003 0.08419 -0.0282 0.0940 1.0000