N-24 (n24-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: N-24 (n24-il) Reynolds number: 200,000 Max Cl/Cd: 65.65 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n24-il-200000.txt Download as CSV file: xf-n24-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.3397 0.06194 0.05819 -0.0915 0.8925 0.0613
-11.500 -0.3341 0.06083 0.05710 -0.0898 0.8847 0.0616
-11.250 -0.3642 0.05247 0.04844 -0.0943 0.8764 0.0600
-11.000 -0.3983 0.04301 0.03832 -0.0967 0.8677 0.0585
-10.750 -0.4083 0.03732 0.03196 -0.0952 0.8623 0.0581
-10.500 -0.3975 0.03382 0.02798 -0.0948 0.8537 0.0583
-10.250 -0.3843 0.03147 0.02525 -0.0930 0.8478 0.0589
-10.000 -0.3672 0.02957 0.02296 -0.0915 0.8418 0.0598
-9.750 -0.3467 0.02784 0.02081 -0.0906 0.8339 0.0608
-9.500 -0.3262 0.02645 0.01921 -0.0890 0.8285 0.0617
-9.250 -0.3018 0.02557 0.01829 -0.0882 0.8219 0.0626
-9.000 -0.2767 0.02473 0.01736 -0.0875 0.8145 0.0638
-8.750 -0.2534 0.02383 0.01630 -0.0861 0.8091 0.0653
-8.500 -0.2273 0.02297 0.01522 -0.0856 0.8016 0.0671
-8.250 -0.2017 0.02206 0.01418 -0.0848 0.7942 0.0690
-8.000 -0.1772 0.02142 0.01352 -0.0836 0.7889 0.0712
-7.750 -0.1489 0.02090 0.01288 -0.0834 0.7800 0.0750
-7.500 -0.1231 0.02016 0.01215 -0.0827 0.7734 0.0790
-7.250 -0.0968 0.01953 0.01138 -0.0820 0.7675 0.0855
-7.000 -0.0690 0.01894 0.01081 -0.0818 0.7589 0.0948
-6.750 -0.0426 0.01850 0.01034 -0.0811 0.7527 0.1047
-6.500 -0.0146 0.01824 0.01014 -0.0810 0.7449 0.1130
-6.250 0.0136 0.01800 0.00984 -0.0808 0.7375 0.1199
-6.000 0.0413 0.01789 0.00964 -0.0803 0.7320 0.1265
-5.750 0.0705 0.01770 0.00944 -0.0805 0.7235 0.1324
-5.500 0.0986 0.01754 0.00923 -0.0802 0.7163 0.1385
-5.250 0.1274 0.01741 0.00898 -0.0800 0.7086 0.1438
-5.000 0.1555 0.01699 0.00860 -0.0798 0.6998 0.1489
-4.750 0.1836 0.01679 0.00831 -0.0795 0.6926 0.1554
-4.500 0.2125 0.01653 0.00806 -0.0796 0.6836 0.1626
-4.250 0.2408 0.01633 0.00783 -0.0794 0.6773 0.1716
-4.000 0.2695 0.01609 0.00764 -0.0795 0.6702 0.1824
-3.750 0.2981 0.01583 0.00741 -0.0795 0.6632 0.1977
-3.500 0.3262 0.01554 0.00716 -0.0793 0.6576 0.2203
-3.250 0.3548 0.01536 0.00710 -0.0795 0.6502 0.2492
-3.000 0.3831 0.01513 0.00698 -0.0795 0.6434 0.2806
-2.750 0.4111 0.01495 0.00686 -0.0794 0.6380 0.3195
-2.500 0.4391 0.01476 0.00692 -0.0796 0.6307 0.3736
-2.250 0.4659 0.01444 0.00688 -0.0794 0.6243 0.4546
-2.000 0.4902 0.01398 0.00687 -0.0785 0.6188 0.5921
-1.750 0.5715 0.01318 0.00701 -0.0888 0.6092 1.0002
-1.500 0.5987 0.01327 0.00690 -0.0886 0.6031 1.0002
-1.250 0.6260 0.01342 0.00696 -0.0886 0.5963 1.0002
-1.000 0.6533 0.01354 0.00697 -0.0885 0.5891 1.0002
-0.750 0.6806 0.01367 0.00690 -0.0883 0.5829 1.0002
-0.500 0.7076 0.01381 0.00703 -0.0883 0.5747 1.0002
-0.250 0.7348 0.01392 0.00701 -0.0882 0.5673 1.0002
0.000 0.7619 0.01410 0.00710 -0.0882 0.5598 1.0002
0.250 0.7889 0.01424 0.00718 -0.0881 0.5517 1.0002
0.500 0.8162 0.01442 0.00720 -0.0881 0.5447 1.0002
0.750 0.8426 0.01458 0.00737 -0.0880 0.5355 1.0002
1.000 0.8698 0.01475 0.00737 -0.0880 0.5278 1.0002
1.250 0.8957 0.01493 0.00757 -0.0879 0.5177 1.0002
1.500 0.9226 0.01512 0.00760 -0.0878 0.5094 1.0002
1.750 0.9481 0.01533 0.00783 -0.0877 0.4990 1.0002
2.000 0.9748 0.01555 0.00789 -0.0876 0.4906 1.0002
2.250 0.9995 0.01578 0.00815 -0.0874 0.4798 1.0002
2.500 1.0255 0.01603 0.00828 -0.0873 0.4710 1.0002
2.750 1.0498 0.01628 0.00853 -0.0871 0.4603 1.0002
3.000 1.0749 0.01657 0.00872 -0.0869 0.4516 1.0002
3.250 1.0990 0.01685 0.00899 -0.0867 0.4420 1.0002
3.500 1.1239 0.01718 0.00922 -0.0865 0.4343 1.0002
3.750 1.1474 0.01750 0.00955 -0.0862 0.4257 1.0002
4.000 1.1725 0.01786 0.00976 -0.0861 0.4189 1.0002
4.250 1.1948 0.01822 0.01018 -0.0856 0.4109 1.0002
4.500 1.2186 0.01857 0.01046 -0.0854 0.4044 1.0002
4.750 1.2423 0.01900 0.01086 -0.0852 0.3984 1.0002
5.000 1.2642 0.01938 0.01126 -0.0847 0.3917 1.0002
5.250 1.2882 0.01979 0.01155 -0.0846 0.3857 1.0002
5.500 1.3088 0.02023 0.01204 -0.0839 0.3793 1.0002
5.750 1.3293 0.02064 0.01245 -0.0833 0.3730 1.0002
6.000 1.3541 0.02112 0.01277 -0.0833 0.3671 1.0002
6.250 1.3704 0.02158 0.01336 -0.0821 0.3610 1.0002
6.500 1.3896 0.02204 0.01382 -0.0813 0.3554 1.0002
6.750 1.4152 0.02256 0.01420 -0.0816 0.3505 1.0002
7.000 1.4320 0.02311 0.01487 -0.0805 0.3462 1.0002
7.250 1.4492 0.02365 0.01547 -0.0795 0.3417 1.0002
7.500 1.4685 0.02417 0.01599 -0.0788 0.3374 1.0002
7.750 1.4974 0.02473 0.01642 -0.0797 0.3330 1.0002
8.000 1.5061 0.02538 0.01723 -0.0774 0.3291 1.0002
8.250 1.5172 0.02603 0.01796 -0.0756 0.3248 1.0002
8.500 1.5329 0.02663 0.01857 -0.0745 0.3204 1.0002
8.750 1.5633 0.02716 0.01898 -0.0757 0.3157 1.0002
9.000 1.5653 0.02803 0.02003 -0.0727 0.3120 1.0002
9.250 1.5742 0.02886 0.02096 -0.0710 0.3076 1.0002
9.500 1.5886 0.02956 0.02169 -0.0700 0.3034 1.0002
9.750 1.6161 0.03008 0.02210 -0.0707 0.2989 1.0002
10.000 1.6170 0.03123 0.02343 -0.0682 0.2951 1.0002
10.250 1.6222 0.03231 0.02464 -0.0663 0.2906 1.0002
10.500 1.6338 0.03318 0.02554 -0.0653 0.2862 1.0002
10.750 1.6593 0.03368 0.02593 -0.0658 0.2816 1.0002
11.000 1.6525 0.03536 0.02785 -0.0630 0.2774 1.0002
11.250 1.6552 0.03675 0.02935 -0.0614 0.2726 1.0002
11.500 1.6656 0.03775 0.03034 -0.0606 0.2680 1.0002
11.750 1.6738 0.03902 0.03166 -0.0596 0.2631 1.0002
12.000 1.6679 0.04110 0.03392 -0.0578 0.2579 1.0002
12.250 1.6720 0.04259 0.03544 -0.0568 0.2528 1.0002
12.500 1.6810 0.04388 0.03670 -0.0561 0.2477 1.0002
12.750 1.6706 0.04663 0.03965 -0.0547 0.2421 1.0002
13.000 1.6719 0.04853 0.04158 -0.0539 0.2367 1.0002
13.250 1.6729 0.05062 0.04370 -0.0532 0.2310 1.0002
13.500 1.6638 0.05380 0.04703 -0.0526 0.2249 1.0002
13.750 1.6694 0.05554 0.04868 -0.0523 0.2192 1.0002
14.000 1.6579 0.05931 0.05263 -0.0519 0.2133 1.0002
14.250 1.6538 0.06235 0.05573 -0.0519 0.2076 1.0002
14.500 1.6567 0.06462 0.05796 -0.0518 0.2024 1.0002
14.750 1.6466 0.06863 0.06214 -0.0519 0.1971 1.0002
15.000 1.6462 0.07141 0.06493 -0.0521 0.1923 1.0002
15.250 1.6481 0.07393 0.06745 -0.0522 0.1879 1.0002
15.500 1.6385 0.07811 0.07178 -0.0527 0.1834 1.0002
15.750 1.6367 0.08124 0.07495 -0.0531 0.1794 1.0002
16.000 1.6480 0.08245 0.07606 -0.0531 0.1755 1.0002
16.250 1.6344 0.08732 0.08115 -0.0538 0.1721 1.0002
16.500 1.6277 0.09125 0.08519 -0.0545 0.1685 1.0002
16.750 1.6296 0.09393 0.08789 -0.0551 0.1652 1.0002
17.000 1.6397 0.09533 0.08922 -0.0553 0.1618 1.0002
17.250 1.6232 0.10082 0.09494 -0.0566 0.1588 1.0002
17.500 1.6139 0.10527 0.09950 -0.0577 0.1555 1.0002
17.750 1.6153 0.10809 0.10235 -0.0586 0.1522 1.0002
18.000 1.6280 0.10906 0.10323 -0.0589 0.1489 1.0002
18.250 1.6074 0.11541 0.10982 -0.0609 0.1463 1.0002
18.500 1.5955 0.12048 0.11504 -0.0626 0.1434 1.0002
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Polar data table (+)
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