NACA 4421 (naca4421-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: NACA 4421 (naca4421-il) Reynolds number: 100,000 Max Cl/Cd: 36.06 at α=9.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca4421-il-100000.txt Download as CSV file: xf-naca4421-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.7343 0.07273 0.06697 -0.0629 1.0000 0.1401
-11.250 -0.8137 0.06750 0.06164 -0.0578 1.0000 0.1388
-11.000 -0.8853 0.06263 0.05653 -0.0512 1.0000 0.1381
-10.750 -0.9303 0.05585 0.04914 -0.0492 0.9953 0.1396
-10.500 -0.9221 0.05203 0.04493 -0.0507 0.9881 0.1430
-10.250 -0.8770 0.05238 0.04550 -0.0536 0.9819 0.1471
-10.000 -0.8704 0.04895 0.04156 -0.0542 0.9739 0.1517
-9.750 -0.8439 0.04712 0.03958 -0.0560 0.9668 0.1560
-9.500 -0.8117 0.04679 0.03932 -0.0574 0.9594 0.1607
-9.250 -0.7970 0.04404 0.03595 -0.0580 0.9514 0.1666
-9.000 -0.7619 0.04391 0.03608 -0.0595 0.9442 0.1710
-8.750 -0.7343 0.04293 0.03493 -0.0605 0.9363 0.1771
-8.500 -0.7022 0.04169 0.03353 -0.0624 0.9302 0.1829
-8.250 -0.6772 0.04140 0.03331 -0.0623 0.9207 0.1879
-8.000 -0.6418 0.03995 0.03144 -0.0648 0.9153 0.1954
-7.750 -0.6213 0.03973 0.03140 -0.0637 0.9050 0.1995
-7.500 -0.5838 0.03908 0.03062 -0.0659 0.8988 0.2066
-7.250 -0.5597 0.03820 0.02958 -0.0659 0.8905 0.2123
-7.000 -0.5283 0.03789 0.02934 -0.0667 0.8824 0.2180
-6.750 -0.4867 0.03704 0.02816 -0.0694 0.8779 0.2265
-6.500 -0.4712 0.03659 0.02784 -0.0676 0.8664 0.2310
-6.250 -0.4319 0.03605 0.02727 -0.0697 0.8607 0.2386
-6.000 -0.3866 0.03503 0.02605 -0.0728 0.8574 0.2474
-5.750 -0.3770 0.03487 0.02598 -0.0700 0.8441 0.2519
-5.500 -0.3347 0.03411 0.02508 -0.0724 0.8396 0.2613
-5.250 -0.3124 0.03360 0.02451 -0.0717 0.8305 0.2680
-5.000 -0.2819 0.03312 0.02411 -0.0721 0.8227 0.2761
-4.750 -0.2373 0.03215 0.02299 -0.0747 0.8190 0.2876
-4.500 -0.2196 0.03203 0.02299 -0.0731 0.8084 0.2952
-4.250 -0.1856 0.03141 0.02224 -0.0740 0.8018 0.3076
-4.000 -0.1396 0.03055 0.02150 -0.0767 0.7988 0.3218
-3.750 -0.0903 0.02956 0.02057 -0.0799 0.7967 0.3378
-3.500 -0.0892 0.03000 0.02094 -0.0756 0.7819 0.3477
-3.250 -0.0427 0.02909 0.02015 -0.0782 0.7789 0.3653
-3.000 0.0049 0.02818 0.01931 -0.0810 0.7764 0.3841
-2.750 0.0077 0.02873 0.01982 -0.0771 0.7628 0.3955
-2.500 0.0505 0.02800 0.01916 -0.0791 0.7589 0.4150
-2.250 0.0963 0.02711 0.01836 -0.0815 0.7560 0.4361
-2.000 0.1045 0.02754 0.01888 -0.0784 0.7439 0.4495
-1.750 0.1410 0.02698 0.01840 -0.0793 0.7388 0.4718
-1.500 0.1841 0.02620 0.01773 -0.0812 0.7355 0.4984
-1.250 0.1979 0.02653 0.01816 -0.0789 0.7256 0.5200
-1.000 0.2264 0.02623 0.01802 -0.0786 0.7187 0.5493
-0.750 0.2676 0.02550 0.01742 -0.0799 0.7149 0.5889
-0.500 0.3112 0.02479 0.01685 -0.0816 0.7120 0.6341
-0.250 0.3033 0.02592 0.01820 -0.0759 0.6986 0.6617
0.000 0.3405 0.02536 0.01777 -0.0762 0.6945 0.7094
0.250 0.3826 0.02474 0.01724 -0.0770 0.6913 0.7571
0.500 0.3726 0.02600 0.01873 -0.0706 0.6787 0.7891
0.750 0.4075 0.02572 0.01849 -0.0703 0.6742 0.8337
1.000 0.4583 0.02531 0.01804 -0.0724 0.6710 0.8723
1.250 0.4664 0.02656 0.01939 -0.0692 0.6600 0.9070
1.500 0.5319 0.02643 0.01915 -0.0751 0.6547 0.9339
1.750 0.6168 0.02591 0.01843 -0.0844 0.6505 0.9506
2.000 0.6711 0.02661 0.01913 -0.0902 0.6408 0.9687
2.250 0.7456 0.02636 0.01876 -0.0988 0.6335 0.9827
2.500 0.8275 0.02574 0.01793 -0.1085 0.6282 0.9936
2.750 0.8309 0.02665 0.01894 -0.1060 0.6185 1.0000
3.000 0.8413 0.02668 0.01889 -0.1035 0.6123 1.0000
3.250 0.8746 0.02635 0.01840 -0.1045 0.6076 1.0000
3.500 0.8390 0.02765 0.01980 -0.0946 0.5989 1.0000
3.750 0.8504 0.02789 0.01998 -0.0920 0.5923 1.0000
4.000 0.8924 0.02753 0.01946 -0.0941 0.5876 1.0000
4.250 0.8693 0.02883 0.02084 -0.0860 0.5795 1.0000
4.500 0.8774 0.02934 0.02132 -0.0828 0.5723 1.0000
4.750 0.9246 0.02891 0.02075 -0.0856 0.5675 1.0000
5.000 0.9165 0.03006 0.02193 -0.0800 0.5600 1.0000
5.250 0.9185 0.03090 0.02279 -0.0760 0.5522 1.0000
5.500 0.9686 0.03036 0.02213 -0.0792 0.5472 1.0000
5.750 0.9727 0.03132 0.02312 -0.0756 0.5401 1.0000
6.000 0.9665 0.03251 0.02435 -0.0706 0.5317 1.0000
6.250 1.0210 0.03180 0.02353 -0.0743 0.5266 1.0000
6.500 1.0261 0.03281 0.02456 -0.0710 0.5195 1.0000
6.750 1.0135 0.03422 0.02604 -0.0652 0.5109 1.0000
7.000 1.0778 0.03319 0.02488 -0.0702 0.5058 1.0000
7.250 1.0670 0.03470 0.02647 -0.0648 0.4981 1.0000
7.500 1.0588 0.03602 0.02784 -0.0597 0.4899 1.0000
7.750 1.1389 0.03441 0.02609 -0.0668 0.4848 1.0000
8.000 1.0909 0.03725 0.02908 -0.0565 0.4760 1.0000
8.250 1.1130 0.03744 0.02926 -0.0556 0.4686 1.0000
8.500 1.2242 0.03452 0.02605 -0.0666 0.4623 1.0000
8.750 1.1309 0.03899 0.03084 -0.0508 0.4528 1.0000
9.000 1.2114 0.03638 0.02804 -0.0566 0.4459 1.0000
9.250 1.2129 0.03744 0.02914 -0.0532 0.4383 1.0000
9.500 1.2034 0.03893 0.03072 -0.0487 0.4300 1.0000
9.750 1.3028 0.03613 0.02763 -0.0573 0.4237 1.0000
10.000 1.2226 0.04060 0.03243 -0.0445 0.4152 1.0000
10.250 1.2641 0.03972 0.03148 -0.0457 0.4083 1.0000
10.500 1.3007 0.03935 0.03104 -0.0465 0.4015 1.0000
10.750 1.2541 0.04302 0.03493 -0.0391 0.3931 1.0000
11.000 1.3456 0.03960 0.03123 -0.0451 0.3865 1.0000
11.250 1.2802 0.04443 0.03636 -0.0363 0.3786 1.0000
11.500 1.3111 0.04394 0.03582 -0.0362 0.3713 1.0000
11.750 1.3406 0.04373 0.03555 -0.0362 0.3641 1.0000
12.000 1.3002 0.04777 0.03979 -0.0309 0.3558 1.0000
12.250 1.3918 0.04360 0.03531 -0.0355 0.3485 1.0000
12.500 1.3078 0.05064 0.04274 -0.0276 0.3404 1.0000
12.750 1.3984 0.04598 0.03775 -0.0312 0.3327 1.0000
13.000 1.3297 0.05250 0.04460 -0.0252 0.3249 1.0000
13.250 1.3874 0.04983 0.04174 -0.0264 0.3167 1.0000
13.500 1.3505 0.05452 0.04663 -0.0230 0.3089 1.0000
13.750 1.3873 0.05337 0.04534 -0.0230 0.3005 1.0000
14.000 1.3659 0.05712 0.04922 -0.0208 0.2927 1.0000
14.250 1.3891 0.05709 0.04911 -0.0202 0.2844 1.0000
14.500 1.3789 0.06014 0.05224 -0.0187 0.2768 1.0000
14.750 1.3814 0.06204 0.05415 -0.0177 0.2689 1.0000
15.000 1.3944 0.06316 0.05523 -0.0170 0.2615 1.0000
15.250 1.3557 0.06932 0.06159 -0.0157 0.2545 1.0000
15.500 1.4194 0.06552 0.05751 -0.0158 0.2471 1.0000
15.750 1.3045 0.08040 0.07292 -0.0150 0.2413 1.0000
16.000 1.4273 0.06950 0.06151 -0.0144 0.2341 1.0000
16.250 1.3383 0.08183 0.07428 -0.0141 0.2295 1.0000
16.750 1.4067 0.07919 0.07139 -0.0130 0.2172 1.0000
17.000 0.8222 0.18607 0.17927 -0.0542 0.1986 1.0000
17.250 0.8199 0.19136 0.18459 -0.0570 0.1989 1.0000
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