N-24 (n24-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: N-24 (n24-il) Reynolds number: 100,000 Max Cl/Cd: 41.49 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n24-il-100000.txt Download as CSV file: xf-n24-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: N-24
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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.0979 0.09928 0.09456 -0.0726 0.9573 0.1497
-10.750 -0.0871 0.09638 0.09166 -0.0757 0.9481 0.1550
-10.500 -0.1401 0.09383 0.08919 -0.0866 0.9299 0.1599
-10.250 -0.0873 0.08933 0.08465 -0.0834 0.9287 0.1619
-10.000 -0.0717 0.08701 0.08233 -0.0821 0.9179 0.1643
-9.750 -0.0648 0.08469 0.08002 -0.0821 0.9072 0.1676
-9.500 -0.2074 0.05918 0.05375 -0.1050 0.8844 0.1047
-9.250 -0.1943 0.05636 0.05088 -0.1046 0.8761 0.1036
-9.000 -0.1889 0.05221 0.04650 -0.1047 0.8670 0.1019
-8.750 -0.1867 0.04739 0.04120 -0.1046 0.8587 0.1011
-8.500 -0.1788 0.04355 0.03685 -0.1038 0.8496 0.1020
-8.250 -0.1598 0.03976 0.03238 -0.1035 0.8451 0.1037
-8.000 -0.1499 0.03765 0.02973 -0.1015 0.8332 0.1053
-7.750 -0.1207 0.03619 0.02831 -0.1014 0.8284 0.1085
-7.500 -0.1020 0.03532 0.02727 -0.1002 0.8190 0.1123
-7.250 -0.0777 0.03383 0.02544 -0.0995 0.8124 0.1189
-7.000 -0.0479 0.03288 0.02425 -0.0989 0.8084 0.1292
-6.750 -0.0298 0.03270 0.02422 -0.0978 0.7976 0.1372
-6.500 -0.0014 0.03179 0.02316 -0.0973 0.7923 0.1490
-6.250 0.0287 0.03108 0.02221 -0.0968 0.7888 0.1609
-6.000 0.0462 0.03136 0.02261 -0.0959 0.7775 0.1685
-5.750 0.0759 0.03074 0.02185 -0.0955 0.7729 0.1795
-5.500 0.1065 0.03033 0.02137 -0.0950 0.7695 0.1923
-5.250 0.1235 0.03060 0.02172 -0.0943 0.7579 0.1998
-5.000 0.1549 0.02987 0.02086 -0.0939 0.7535 0.2093
-4.750 0.1800 0.02939 0.02032 -0.0932 0.7455 0.2163
-4.500 0.2075 0.02877 0.01970 -0.0925 0.7376 0.2243
-4.250 0.2403 0.02764 0.01845 -0.0919 0.7333 0.2348
-4.000 0.2622 0.02765 0.01854 -0.0912 0.7233 0.2470
-3.750 0.2913 0.02695 0.01789 -0.0907 0.7176 0.2668
-3.500 0.3224 0.02601 0.01703 -0.0901 0.7139 0.2956
-3.250 0.3423 0.02627 0.01749 -0.0895 0.7036 0.3254
-3.000 0.3713 0.02557 0.01695 -0.0889 0.6983 0.3694
-2.750 0.4023 0.02459 0.01623 -0.0883 0.6947 0.4358
-2.500 0.4210 0.02469 0.01690 -0.0874 0.6842 0.5390
-2.250 0.5077 0.02286 0.01607 -0.0964 0.6792 1.0002
-2.000 0.5358 0.02269 0.01562 -0.0958 0.6739 1.0002
-1.750 0.5568 0.02321 0.01601 -0.0950 0.6639 1.0002
-1.500 0.5867 0.02286 0.01543 -0.0945 0.6588 1.0002
-1.250 0.6083 0.02337 0.01584 -0.0938 0.6495 1.0002
-1.000 0.6360 0.02324 0.01554 -0.0933 0.6426 1.0002
-0.750 0.6658 0.02300 0.01510 -0.0929 0.6369 1.0002
-0.500 0.6871 0.02347 0.01552 -0.0921 0.6263 1.0002
-0.250 0.7188 0.02307 0.01491 -0.0919 0.6208 1.0002
0.000 0.7391 0.02368 0.01550 -0.0911 0.6099 1.0002
0.250 0.7700 0.02339 0.01503 -0.0909 0.6035 1.0002
0.500 0.7922 0.02383 0.01544 -0.0903 0.5930 1.0002
0.750 0.8223 0.02362 0.01506 -0.0901 0.5855 1.0002
1.000 0.8452 0.02402 0.01542 -0.0895 0.5752 1.0002
1.250 0.8745 0.02393 0.01518 -0.0893 0.5672 1.0002
1.500 0.8976 0.02439 0.01560 -0.0888 0.5572 1.0002
1.750 0.9262 0.02440 0.01548 -0.0887 0.5489 1.0002
2.000 0.9492 0.02486 0.01591 -0.0882 0.5389 1.0002
2.250 0.9772 0.02494 0.01586 -0.0881 0.5305 1.0002
2.500 1.0001 0.02545 0.01635 -0.0876 0.5211 1.0002
2.750 1.0262 0.02572 0.01654 -0.0874 0.5129 1.0002
3.000 1.0520 0.02614 0.01688 -0.0873 0.5053 1.0002
3.250 1.0732 0.02671 0.01747 -0.0866 0.4963 1.0002
3.500 1.1069 0.02668 0.01722 -0.0874 0.4907 1.0002
3.750 1.1194 0.02776 0.01847 -0.0859 0.4810 1.0002
4.000 1.1482 0.02796 0.01858 -0.0861 0.4750 1.0002
4.250 1.1694 0.02872 0.01935 -0.0856 0.4684 1.0002
4.500 1.1877 0.02949 0.02018 -0.0848 0.4610 1.0002
4.750 1.2197 0.02956 0.02011 -0.0855 0.4559 1.0002
5.000 1.2329 0.03070 0.02137 -0.0841 0.4490 1.0002
5.250 1.2517 0.03148 0.02221 -0.0834 0.4429 1.0002
5.500 1.2844 0.03156 0.02217 -0.0842 0.4382 1.0002
5.750 1.2957 0.03281 0.02354 -0.0827 0.4321 1.0002
6.000 1.3094 0.03381 0.02464 -0.0814 0.4260 1.0002
6.250 1.3416 0.03388 0.02462 -0.0822 0.4213 1.0002
6.500 1.3556 0.03489 0.02570 -0.0810 0.4154 1.0002
6.750 1.3643 0.03589 0.02680 -0.0790 0.4085 1.0002
7.000 1.4083 0.03516 0.02585 -0.0811 0.4028 1.0002
7.250 1.4042 0.03687 0.02777 -0.0777 0.3963 1.0002
7.500 1.4180 0.03761 0.02857 -0.0764 0.3902 1.0002
7.750 1.4650 0.03704 0.02781 -0.0791 0.3853 1.0002
8.000 1.4518 0.03923 0.03025 -0.0747 0.3799 1.0002
8.250 1.4481 0.04081 0.03196 -0.0714 0.3744 1.0002
8.500 1.4966 0.04019 0.03121 -0.0743 0.3692 1.0002
8.750 1.4968 0.04178 0.03291 -0.0716 0.3644 1.0002
9.000 1.4556 0.04531 0.03670 -0.0647 0.3593 1.0002
9.250 1.4837 0.04544 0.03680 -0.0651 0.3541 1.0002
9.500 1.5440 0.04441 0.03564 -0.0690 0.3490 1.0002
9.750 1.2110 0.07645 0.06849 -0.0519 0.3344 1.0002
10.000 1.3946 0.05821 0.05006 -0.0544 0.3376 1.0002
10.250 1.5785 0.04761 0.03897 -0.0655 0.3327 1.0002
10.750 1.2754 0.07985 0.07204 -0.0502 0.3155 1.0002
11.000 1.3751 0.07032 0.06244 -0.0504 0.3146 1.0002
11.250 0.9620 0.13793 0.13036 -0.0613 0.2670 1.0002
11.500 1.0002 0.13521 0.12767 -0.0597 0.2656 1.0002
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Polar data table (+)
Polar graphs
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