NACA 4421 (naca4421-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 4421 (naca4421-il) Reynolds number: 100,000 Max Cl/Cd: 41.85 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca4421-il-100000-n5.txt Download as CSV file: xf-naca4421-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.7162 0.07173 0.06475 -0.0867 1.0000 0.0912
-14.250 -0.7909 0.06184 0.05454 -0.0897 1.0000 0.0918
-14.000 -0.8364 0.05663 0.04912 -0.0893 1.0000 0.0925
-13.750 -0.8749 0.05286 0.04515 -0.0872 1.0000 0.0932
-13.500 -0.8749 0.05134 0.04367 -0.0865 0.9984 0.0943
-13.250 -0.8633 0.04920 0.04147 -0.0888 0.9938 0.0961
-13.000 -0.8587 0.04671 0.03881 -0.0905 0.9880 0.0982
-12.750 -0.8586 0.04413 0.03594 -0.0915 0.9812 0.1006
-12.500 -0.8475 0.04276 0.03452 -0.0917 0.9752 0.1026
-12.250 -0.8346 0.04169 0.03342 -0.0915 0.9686 0.1048
-12.000 -0.8199 0.04030 0.03186 -0.0918 0.9633 0.1077
-11.750 -0.8120 0.03889 0.03024 -0.0906 0.9547 0.1105
-11.500 -0.7851 0.03806 0.02946 -0.0918 0.9504 0.1133
-11.250 -0.7717 0.03714 0.02844 -0.0907 0.9426 0.1163
-11.000 -0.7530 0.03592 0.02700 -0.0906 0.9363 0.1200
-10.750 -0.7223 0.03518 0.02631 -0.0921 0.9328 0.1232
-10.500 -0.7107 0.03450 0.02555 -0.0900 0.9236 0.1264
-10.250 -0.6862 0.03351 0.02436 -0.0905 0.9183 0.1306
-10.000 -0.6531 0.03279 0.02369 -0.0921 0.9152 0.1343
-9.750 -0.6414 0.03224 0.02306 -0.0898 0.9053 0.1377
-9.500 -0.6138 0.03140 0.02206 -0.0904 0.9003 0.1422
-9.250 -0.5795 0.03071 0.02141 -0.0920 0.8971 0.1463
-9.000 -0.5657 0.03023 0.02086 -0.0898 0.8877 0.1501
-8.750 -0.5379 0.02951 0.02003 -0.0902 0.8822 0.1546
-8.500 -0.5047 0.02887 0.01942 -0.0915 0.8786 0.1590
-8.250 -0.4859 0.02842 0.01889 -0.0900 0.8704 0.1635
-8.000 -0.4608 0.02785 0.01827 -0.0897 0.8637 0.1681
-7.750 -0.4282 0.02728 0.01771 -0.0907 0.8596 0.1732
-7.500 -0.4033 0.02680 0.01712 -0.0903 0.8530 0.1788
-7.250 -0.3818 0.02639 0.01675 -0.0892 0.8446 0.1832
-7.000 -0.3494 0.02585 0.01619 -0.0901 0.8400 0.1890
-6.750 -0.3173 0.02529 0.01554 -0.0908 0.8353 0.1954
-6.500 -0.3005 0.02505 0.01535 -0.0888 0.8250 0.1996
-6.000 -0.2360 0.02403 0.01425 -0.0903 0.8147 0.2131
-5.750 -0.2182 0.02383 0.01406 -0.0884 0.8043 0.2189
-5.500 -0.1851 0.02336 0.01348 -0.0892 0.7987 0.2273
-5.250 -0.1580 0.02299 0.01316 -0.0890 0.7917 0.2343
-5.000 -0.1347 0.02274 0.01285 -0.0880 0.7825 0.2428
-4.750 -0.1016 0.02226 0.01239 -0.0888 0.7768 0.2516
-4.500 -0.0786 0.02206 0.01215 -0.0879 0.7678 0.2606
-4.250 -0.0515 0.02174 0.01185 -0.0876 0.7597 0.2697
-4.000 -0.0169 0.02133 0.01140 -0.0886 0.7541 0.2810
-3.750 0.0021 0.02121 0.01132 -0.0870 0.7434 0.2898
-3.500 0.0324 0.02092 0.01101 -0.0872 0.7361 0.3012
-3.250 0.0597 0.02069 0.01080 -0.0870 0.7284 0.3121
-3.000 0.0840 0.02055 0.01066 -0.0863 0.7191 0.3239
-2.750 0.1164 0.02024 0.01036 -0.0869 0.7125 0.3370
-2.500 0.1380 0.02021 0.01033 -0.0857 0.7026 0.3500
-2.250 0.1660 0.02000 0.01017 -0.0855 0.6948 0.3647
-2.000 0.1944 0.01984 0.01002 -0.0855 0.6876 0.3807
-1.750 0.2173 0.01979 0.01001 -0.0845 0.6783 0.3976
-1.500 0.2477 0.01960 0.00983 -0.0848 0.6714 0.4182
-1.250 0.2704 0.01955 0.00987 -0.0838 0.6627 0.4388
-1.000 0.2959 0.01946 0.00985 -0.0832 0.6548 0.4624
-0.750 0.3271 0.01929 0.00970 -0.0836 0.6489 0.4903
-0.500 0.3467 0.01933 0.00989 -0.0820 0.6398 0.5170
-0.250 0.3728 0.01925 0.00991 -0.0814 0.6325 0.5473
0.000 0.4013 0.01918 0.00989 -0.0812 0.6262 0.5804
0.250 0.4222 0.01927 0.01011 -0.0798 0.6181 0.6121
0.500 0.4484 0.01927 0.01019 -0.0792 0.6115 0.6451
0.750 0.4773 0.01928 0.01021 -0.0790 0.6055 0.6791
1.000 0.4971 0.01943 0.01047 -0.0773 0.5977 0.7106
1.250 0.5225 0.01950 0.01060 -0.0764 0.5911 0.7428
1.500 0.5531 0.01954 0.01063 -0.0764 0.5859 0.7756
1.750 0.5722 0.01978 0.01099 -0.0746 0.5783 0.8066
2.000 0.5994 0.01994 0.01119 -0.0740 0.5714 0.8375
2.250 0.6351 0.02007 0.01125 -0.0750 0.5658 0.8679
2.500 0.6620 0.02038 0.01163 -0.0748 0.5580 0.8974
2.750 0.6957 0.02062 0.01183 -0.0759 0.5507 0.9236
3.000 0.7400 0.02080 0.01189 -0.0789 0.5447 0.9454
3.250 0.7785 0.02119 0.01232 -0.0813 0.5368 0.9691
3.500 0.8280 0.02149 0.01257 -0.0859 0.5295 0.9881
3.750 0.8812 0.02168 0.01262 -0.0910 0.5236 1.0000
4.000 0.8831 0.02196 0.01294 -0.0867 0.5171 1.0000
4.250 0.8937 0.02218 0.01313 -0.0838 0.5110 1.0000
4.500 0.9120 0.02235 0.01320 -0.0821 0.5057 1.0000
4.750 0.9275 0.02260 0.01340 -0.0800 0.5003 1.0000
5.000 0.9357 0.02295 0.01378 -0.0767 0.4939 1.0000
5.250 0.9527 0.02321 0.01399 -0.0749 0.4881 1.0000
5.500 0.9789 0.02339 0.01406 -0.0746 0.4831 1.0000
5.750 0.9854 0.02386 0.01459 -0.0711 0.4767 1.0000
6.000 0.9985 0.02422 0.01496 -0.0687 0.4705 1.0000
6.250 1.0205 0.02447 0.01513 -0.0677 0.4650 1.0000
6.500 1.0352 0.02486 0.01552 -0.0657 0.4593 1.0000
6.750 1.0430 0.02538 0.01609 -0.0625 0.4527 1.0000
7.000 1.0615 0.02571 0.01640 -0.0611 0.4469 1.0000
7.250 1.0842 0.02602 0.01664 -0.0604 0.4415 1.0000
7.500 1.0881 0.02674 0.01747 -0.0569 0.4345 1.0000
7.750 1.1040 0.02719 0.01791 -0.0552 0.4282 1.0000
8.000 1.1288 0.02743 0.01807 -0.0549 0.4228 1.0000
8.250 1.1299 0.02837 0.01914 -0.0513 0.4154 1.0000
8.500 1.1440 0.02890 0.01967 -0.0496 0.4086 1.0000
8.750 1.1591 0.02940 0.02014 -0.0480 0.4015 1.0000
9.000 1.1615 0.03039 0.02121 -0.0450 0.3929 1.0000
9.250 1.1812 0.03068 0.02139 -0.0439 0.3856 1.0000
9.500 1.1785 0.03206 0.02291 -0.0407 0.3767 1.0000
9.750 1.1913 0.03273 0.02355 -0.0392 0.3693 1.0000
10.000 1.1969 0.03390 0.02478 -0.0371 0.3617 1.0000
10.250 1.2033 0.03506 0.02598 -0.0352 0.3541 1.0000
10.500 1.2164 0.03585 0.02675 -0.0339 0.3475 1.0000
10.750 1.2163 0.03756 0.02857 -0.0318 0.3395 1.0000
11.000 1.2293 0.03840 0.02936 -0.0306 0.3329 1.0000
11.250 1.2290 0.04028 0.03135 -0.0287 0.3251 1.0000
11.500 1.2355 0.04167 0.03276 -0.0274 0.3179 1.0000
11.750 1.2412 0.04321 0.03432 -0.0261 0.3109 1.0000
12.000 1.2417 0.04522 0.03640 -0.0247 0.3033 1.0000
12.250 1.2528 0.04634 0.03746 -0.0237 0.2968 1.0000
12.500 1.2478 0.04905 0.04030 -0.0225 0.2889 1.0000
12.750 1.2576 0.05034 0.04155 -0.0216 0.2823 1.0000
13.000 1.2541 0.05307 0.04438 -0.0206 0.2749 1.0000
13.250 1.2581 0.05506 0.04638 -0.0199 0.2679 1.0000
13.500 1.2604 0.05730 0.04864 -0.0192 0.2611 1.0000
13.750 1.2578 0.06013 0.05155 -0.0186 0.2537 1.0000
14.000 1.2660 0.06175 0.05312 -0.0180 0.2475 1.0000
14.250 1.2571 0.06549 0.05700 -0.0177 0.2399 1.0000
14.500 1.2664 0.06702 0.05846 -0.0173 0.2338 1.0000
14.750 1.2562 0.07108 0.06267 -0.0172 0.2265 1.0000
15.000 1.2593 0.07344 0.06503 -0.0170 0.2201 1.0000
15.250 1.2556 0.07679 0.06845 -0.0171 0.2136 1.0000
15.500 1.2529 0.08003 0.07174 -0.0172 0.2072 1.0000
15.750 1.2576 0.08229 0.07398 -0.0171 0.2016 1.0000
16.000 1.2485 0.08653 0.07835 -0.0176 0.1952 1.0000
16.250 1.2579 0.08814 0.07989 -0.0175 0.1902 1.0000
16.500 1.2477 0.09265 0.08453 -0.0183 0.1844 1.0000
16.750 1.2482 0.09562 0.08753 -0.0187 0.1793 1.0000
17.000 1.2542 0.09779 0.08968 -0.0189 0.1748 1.0000
17.250 1.2435 0.10253 0.09455 -0.0200 0.1695 1.0000
17.500 1.2502 0.10460 0.09659 -0.0203 0.1652 1.0000
17.750 1.2450 0.10854 0.10060 -0.0213 0.1605 1.0000
18.000 1.2388 0.11269 0.10483 -0.0225 0.1557 1.0000
18.250 1.2530 0.11360 0.10565 -0.0226 0.1519 1.0000
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Polar data table (+)
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