NACA 4421 (naca4421-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 4421 (naca4421-il) Reynolds number: 200,000 Max Cl/Cd: 61.22 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca4421-il-200000.txt Download as CSV file: xf-naca4421-il-200000.csv |
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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.250 -0.8642 0.06424 0.05861 -0.1012 1.0000 0.0823
-16.000 -0.9048 0.05865 0.05282 -0.1021 1.0000 0.0827
-15.750 -0.9373 0.05457 0.04858 -0.1015 1.0000 0.0831
-15.500 -0.9666 0.05133 0.04519 -0.0999 1.0000 0.0837
-15.250 -0.9952 0.04863 0.04234 -0.0973 1.0000 0.0842
-15.000 -1.0239 0.04636 0.03992 -0.0939 1.0000 0.0847
-14.750 -1.0533 0.04448 0.03788 -0.0896 1.0000 0.0851
-14.500 -1.0833 0.04298 0.03621 -0.0843 1.0000 0.0855
-14.250 -1.0938 0.04196 0.03518 -0.0803 1.0000 0.0863
-14.000 -1.0974 0.04133 0.03462 -0.0767 0.9999 0.0871
-13.750 -1.0746 0.04045 0.03376 -0.0779 0.9961 0.0888
-13.500 -1.0601 0.03928 0.03244 -0.0784 0.9918 0.0907
-13.250 -1.0511 0.03775 0.03062 -0.0779 0.9851 0.0927
-13.000 -1.0216 0.03669 0.02960 -0.0796 0.9815 0.0947
-12.750 -0.9884 0.03598 0.02892 -0.0818 0.9788 0.0971
-12.500 -0.9744 0.03495 0.02773 -0.0809 0.9711 0.0995
-12.250 -0.9473 0.03376 0.02640 -0.0822 0.9668 0.1023
-12.000 -0.9096 0.03317 0.02591 -0.0849 0.9645 0.1053
-11.750 -0.8964 0.03241 0.02502 -0.0832 0.9557 0.1081
-11.500 -0.8659 0.03139 0.02390 -0.0847 0.9518 0.1116
-11.250 -0.8271 0.03078 0.02335 -0.0874 0.9495 0.1153
-11.000 -0.8153 0.03018 0.02258 -0.0851 0.9401 0.1186
-10.750 -0.7814 0.02934 0.02179 -0.0868 0.9363 0.1225
-10.500 -0.7435 0.02873 0.02115 -0.0892 0.9337 0.1272
-10.250 -0.7276 0.02813 0.02039 -0.0875 0.9256 0.1309
-10.000 -0.6949 0.02755 0.01994 -0.0888 0.9209 0.1350
-9.750 -0.6591 0.02695 0.01918 -0.0906 0.9178 0.1403
-9.500 -0.6179 0.02613 0.01844 -0.0935 0.9159 0.1452
-9.250 -0.6010 0.02583 0.01812 -0.0916 0.9072 0.1491
-9.000 -0.5691 0.02524 0.01736 -0.0925 0.9025 0.1539
-8.750 -0.5279 0.02449 0.01675 -0.0952 0.9002 0.1589
-8.500 -0.4880 0.02388 0.01604 -0.0975 0.8981 0.1645
-8.250 -0.4476 0.02306 0.01524 -0.1000 0.8963 0.1695
-8.000 -0.4353 0.02287 0.01509 -0.0970 0.8852 0.1730
-7.750 -0.3994 0.02231 0.01443 -0.0984 0.8816 0.1784
-7.500 -0.3609 0.02154 0.01370 -0.1004 0.8789 0.1837
-7.250 -0.3346 0.02120 0.01338 -0.0999 0.8723 0.1885
-7.000 -0.3089 0.02085 0.01293 -0.0994 0.8648 0.1938
-6.750 -0.2735 0.02020 0.01235 -0.1006 0.8607 0.1996
-6.500 -0.2356 0.01972 0.01183 -0.1023 0.8575 0.2067
-6.250 -0.2184 0.01949 0.01158 -0.1002 0.8467 0.2121
-6.000 -0.1855 0.01901 0.01116 -0.1009 0.8412 0.2187
-5.750 -0.1489 0.01861 0.01061 -0.1022 0.8370 0.2268
-5.500 -0.1306 0.01828 0.01041 -0.1003 0.8260 0.2331
-5.250 -0.0978 0.01790 0.00997 -0.1010 0.8197 0.2423
-5.000 -0.0704 0.01750 0.00960 -0.1007 0.8121 0.2512
-4.750 -0.0448 0.01727 0.00935 -0.1001 0.8029 0.2611
-4.500 -0.0121 0.01678 0.00887 -0.1008 0.7966 0.2721
-4.250 0.0101 0.01665 0.00873 -0.0995 0.7859 0.2828
-4.000 0.0397 0.01627 0.00838 -0.0997 0.7779 0.2945
-3.500 0.0923 0.01586 0.00799 -0.0987 0.7596 0.3180
-3.250 0.1225 0.01567 0.00773 -0.0990 0.7518 0.3304
-3.000 0.1456 0.01553 0.00766 -0.0979 0.7410 0.3421
-2.750 0.1766 0.01532 0.00740 -0.0983 0.7332 0.3554
-2.500 0.1993 0.01526 0.00738 -0.0972 0.7225 0.3684
-2.250 0.2278 0.01508 0.00721 -0.0971 0.7143 0.3825
-2.000 0.2530 0.01501 0.00716 -0.0965 0.7050 0.3979
-1.750 0.2792 0.01490 0.00707 -0.0960 0.6959 0.4159
-1.500 0.3066 0.01479 0.00700 -0.0958 0.6876 0.4364
-1.250 0.3301 0.01469 0.00700 -0.0948 0.6781 0.4592
-1.000 0.3590 0.01459 0.00691 -0.0949 0.6708 0.4878
-0.750 0.3813 0.01453 0.00700 -0.0937 0.6619 0.5176
-0.500 0.4063 0.01442 0.00702 -0.0930 0.6538 0.5519
-0.250 0.4332 0.01440 0.00707 -0.0926 0.6465 0.5897
0.000 0.4551 0.01438 0.00722 -0.0912 0.6380 0.6274
0.250 0.4814 0.01437 0.00729 -0.0906 0.6311 0.6660
0.500 0.5063 0.01444 0.00744 -0.0897 0.6241 0.7022
0.750 0.5290 0.01447 0.00758 -0.0884 0.6162 0.7357
1.000 0.5554 0.01451 0.00766 -0.0877 0.6095 0.7683
1.250 0.5789 0.01463 0.00786 -0.0864 0.6024 0.8000
1.500 0.6013 0.01472 0.00802 -0.0849 0.5946 0.8305
1.750 0.6286 0.01486 0.00812 -0.0842 0.5882 0.8588
2.000 0.6539 0.01508 0.00839 -0.0832 0.5813 0.8857
2.250 0.6823 0.01529 0.00862 -0.0829 0.5741 0.9104
2.500 0.7187 0.01552 0.00876 -0.0842 0.5679 0.9308
2.750 0.7561 0.01583 0.00903 -0.0860 0.5613 0.9478
3.000 0.7952 0.01609 0.00928 -0.0883 0.5541 0.9625
3.250 0.8459 0.01633 0.00942 -0.0929 0.5474 0.9710
3.500 0.8941 0.01664 0.00968 -0.0972 0.5407 0.9805
3.750 0.9427 0.01688 0.00992 -0.1016 0.5331 0.9907
4.250 1.0212 0.01726 0.01016 -0.1070 0.5207 1.0000
4.500 1.0287 0.01739 0.01032 -0.1035 0.5147 1.0000
4.750 1.0424 0.01751 0.01040 -0.1011 0.5090 1.0000
5.000 1.0653 0.01773 0.01048 -0.1003 0.5037 1.0000
5.250 1.0729 0.01794 0.01076 -0.0967 0.4981 1.0000
5.500 1.0853 0.01812 0.01095 -0.0938 0.4920 1.0000
5.750 1.1048 0.01829 0.01104 -0.0923 0.4863 1.0000
6.000 1.1250 0.01858 0.01128 -0.0910 0.4807 1.0000
6.250 1.1343 0.01881 0.01156 -0.0876 0.4745 1.0000
6.500 1.1521 0.01900 0.01172 -0.0858 0.4683 1.0000
6.750 1.1796 0.01927 0.01187 -0.0859 0.4622 1.0000
7.000 1.1849 0.01951 0.01221 -0.0817 0.4552 1.0000
7.250 1.2000 0.01966 0.01232 -0.0794 0.4477 1.0000
7.500 1.2183 0.01990 0.01249 -0.0778 0.4402 1.0000
7.750 1.2230 0.02013 0.01279 -0.0736 0.4325 1.0000
8.000 1.2411 0.02035 0.01292 -0.0720 0.4257 1.0000
8.250 1.2533 0.02073 0.01333 -0.0694 0.4190 1.0000
8.500 1.2631 0.02108 0.01372 -0.0665 0.4118 1.0000
8.750 1.2850 0.02138 0.01391 -0.0656 0.4051 1.0000
9.000 1.2918 0.02189 0.01452 -0.0624 0.3980 1.0000
9.250 1.3035 0.02232 0.01496 -0.0600 0.3908 1.0000
9.500 1.3228 0.02273 0.01529 -0.0589 0.3841 1.0000
9.750 1.3283 0.02338 0.01605 -0.0558 0.3765 1.0000
10.000 1.3432 0.02386 0.01647 -0.0542 0.3696 1.0000
10.250 1.3534 0.02454 0.01720 -0.0520 0.3623 1.0000
10.500 1.3621 0.02525 0.01795 -0.0496 0.3548 1.0000
10.750 1.3776 0.02585 0.01847 -0.0483 0.3478 1.0000
11.000 1.3822 0.02681 0.01954 -0.0457 0.3401 1.0000
11.250 1.3954 0.02752 0.02017 -0.0442 0.3331 1.0000
11.500 1.4012 0.02859 0.02133 -0.0420 0.3255 1.0000
11.750 1.4092 0.02957 0.02231 -0.0401 0.3180 1.0000
12.000 1.4172 0.03065 0.02340 -0.0383 0.3106 1.0000
12.250 1.4224 0.03190 0.02469 -0.0364 0.3028 1.0000
12.500 1.4312 0.03303 0.02577 -0.0349 0.2956 1.0000
12.750 1.4335 0.03457 0.02740 -0.0330 0.2877 1.0000
13.000 1.4423 0.03577 0.02850 -0.0316 0.2803 1.0000
13.250 1.4417 0.03767 0.03052 -0.0299 0.2722 1.0000
13.500 1.4501 0.03897 0.03170 -0.0286 0.2646 1.0000
13.750 1.4475 0.04122 0.03410 -0.0271 0.2565 1.0000
14.000 1.4543 0.04272 0.03546 -0.0259 0.2488 1.0000
14.250 1.4494 0.04535 0.03825 -0.0246 0.2405 1.0000
14.500 1.4536 0.04715 0.03993 -0.0235 0.2328 1.0000
14.750 1.4480 0.05007 0.04300 -0.0226 0.2245 1.0000
15.000 1.4493 0.05227 0.04510 -0.0217 0.2170 1.0000
15.250 1.4441 0.05536 0.04830 -0.0211 0.2091 1.0000
15.500 1.4446 0.05775 0.05062 -0.0204 0.2022 1.0000
15.750 1.4401 0.06092 0.05389 -0.0201 0.1951 1.0000
16.000 1.4426 0.06317 0.05603 -0.0196 0.1892 1.0000
16.250 1.4393 0.06634 0.05934 -0.0194 0.1833 1.0000
16.500 1.4409 0.06884 0.06180 -0.0192 0.1782 1.0000
16.750 1.4423 0.07140 0.06439 -0.0190 0.1733 1.0000
17.000 1.4412 0.07437 0.06743 -0.0190 0.1686 1.0000
17.250 1.4477 0.07625 0.06922 -0.0187 0.1644 1.0000
17.500 1.4463 0.07932 0.07240 -0.0189 0.1603 1.0000
17.750 1.4463 0.08223 0.07537 -0.0191 0.1563 1.0000
18.000 1.4538 0.08400 0.07705 -0.0189 0.1526 1.0000
18.250 1.4530 0.08700 0.08015 -0.0192 0.1491 1.0000
18.500 1.4523 0.09006 0.08330 -0.0196 0.1455 1.0000
18.750 1.4567 0.09234 0.08556 -0.0198 0.1422 1.0000
19.000 1.4636 0.09424 0.08743 -0.0198 0.1390 1.0000
19.250 1.4589 0.09792 0.09126 -0.0206 0.1359 1.0000
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