N-24 (n24-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: N-24 (n24-il) Reynolds number: 200,000 Max Cl/Cd: 64.59 at α=3° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n24-il-200000-n5.txt Download as CSV file: xf-n24-il-200000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.6802 0.04492 0.03981 -0.0948 0.8847 0.0356
-14.000 -0.6961 0.04150 0.03609 -0.0945 0.8763 0.0357
-13.750 -0.6977 0.03880 0.03310 -0.0939 0.8687 0.0359
-13.500 -0.6944 0.03663 0.03065 -0.0925 0.8632 0.0361
-13.250 -0.6829 0.03466 0.02844 -0.0919 0.8563 0.0363
-13.000 -0.6698 0.03298 0.02652 -0.0908 0.8499 0.0365
-12.750 -0.6556 0.03152 0.02482 -0.0894 0.8448 0.0367
-12.500 -0.6371 0.03019 0.02328 -0.0886 0.8386 0.0369
-12.250 -0.6176 0.02897 0.02197 -0.0877 0.8321 0.0372
-12.000 -0.5983 0.02791 0.02082 -0.0865 0.8266 0.0375
-11.750 -0.5771 0.02694 0.01976 -0.0856 0.8211 0.0378
-11.500 -0.5541 0.02602 0.01875 -0.0850 0.8146 0.0381
-11.250 -0.5319 0.02515 0.01777 -0.0841 0.8087 0.0385
-11.000 -0.5093 0.02434 0.01683 -0.0831 0.8033 0.0389
-10.750 -0.4843 0.02355 0.01596 -0.0827 0.7960 0.0394
-10.500 -0.4602 0.02283 0.01511 -0.0819 0.7898 0.0399
-10.250 -0.4358 0.02215 0.01429 -0.0811 0.7844 0.0406
-10.000 -0.4093 0.02151 0.01355 -0.0808 0.7773 0.0413
-9.750 -0.3840 0.02087 0.01285 -0.0802 0.7710 0.0420
-9.500 -0.3584 0.02032 0.01222 -0.0796 0.7652 0.0428
-9.250 -0.3311 0.01980 0.01165 -0.0794 0.7574 0.0436
-9.000 -0.3047 0.01931 0.01106 -0.0789 0.7508 0.0445
-8.750 -0.2774 0.01885 0.01052 -0.0785 0.7440 0.0456
-8.500 -0.2496 0.01843 0.01006 -0.0783 0.7367 0.0468
-8.250 -0.2224 0.01806 0.00963 -0.0779 0.7305 0.0484
-8.000 -0.1939 0.01772 0.00927 -0.0778 0.7233 0.0507
-7.750 -0.1656 0.01743 0.00896 -0.0776 0.7159 0.0538
-7.500 -0.1375 0.01718 0.00865 -0.0773 0.7094 0.0586
-7.250 -0.1082 0.01698 0.00840 -0.0773 0.7011 0.0652
-7.000 -0.0796 0.01679 0.00810 -0.0771 0.6941 0.0718
-6.750 -0.0506 0.01661 0.00783 -0.0771 0.6872 0.0776
-6.500 -0.0218 0.01639 0.00757 -0.0771 0.6799 0.0825
-6.250 0.0066 0.01618 0.00728 -0.0769 0.6736 0.0868
-6.000 0.0357 0.01599 0.00707 -0.0770 0.6660 0.0913
-5.750 0.0645 0.01582 0.00683 -0.0770 0.6585 0.0953
-5.500 0.0932 0.01564 0.00663 -0.0770 0.6513 0.0992
-5.250 0.1222 0.01551 0.00644 -0.0770 0.6426 0.1034
-5.000 0.1508 0.01537 0.00625 -0.0770 0.6344 0.1082
-4.750 0.1799 0.01525 0.00611 -0.0771 0.6244 0.1131
-4.500 0.2085 0.01514 0.00594 -0.0771 0.6161 0.1187
-4.250 0.2377 0.01504 0.00584 -0.0772 0.6073 0.1259
-4.000 0.2664 0.01495 0.00573 -0.0773 0.6003 0.1351
-3.750 0.2954 0.01486 0.00566 -0.0775 0.5935 0.1467
-3.500 0.3243 0.01478 0.00559 -0.0776 0.5866 0.1609
-3.250 0.3530 0.01472 0.00550 -0.0777 0.5808 0.1759
-3.000 0.3820 0.01466 0.00547 -0.0779 0.5745 0.1913
-2.750 0.4108 0.01459 0.00544 -0.0781 0.5678 0.2084
-2.500 0.4392 0.01456 0.00539 -0.0782 0.5617 0.2278
-2.250 0.4679 0.01450 0.00541 -0.0784 0.5551 0.2513
-2.000 0.4963 0.01444 0.00543 -0.0786 0.5489 0.2808
-1.750 0.5243 0.01438 0.00544 -0.0787 0.5433 0.3209
-1.500 0.5523 0.01428 0.00551 -0.0789 0.5370 0.3691
-1.250 0.5797 0.01417 0.00557 -0.0789 0.5302 0.4265
-1.000 0.6058 0.01399 0.00562 -0.0787 0.5240 0.5159
-0.750 0.6304 0.01365 0.00575 -0.0781 0.5173 0.6526
-0.250 0.7296 0.01338 0.00601 -0.0870 0.5023 1.0002
0.250 0.7828 0.01372 0.00618 -0.0868 0.4877 1.0002
0.500 0.8093 0.01389 0.00630 -0.0868 0.4797 1.0002
0.750 0.8354 0.01408 0.00640 -0.0867 0.4714 1.0002
1.000 0.8615 0.01428 0.00654 -0.0866 0.4635 1.0002
1.250 0.8874 0.01448 0.00668 -0.0864 0.4549 1.0002
1.500 0.9129 0.01470 0.00684 -0.0863 0.4466 1.0002
1.750 0.9381 0.01493 0.00701 -0.0861 0.4371 1.0002
2.000 0.9629 0.01518 0.00720 -0.0859 0.4278 1.0002
2.250 0.9871 0.01545 0.00740 -0.0855 0.4176 1.0002
2.500 1.0111 0.01573 0.00763 -0.0852 0.4078 1.0002
2.750 1.0341 0.01606 0.00787 -0.0847 0.3987 1.0002
3.000 1.0574 0.01637 0.00814 -0.0844 0.3900 1.0002
3.250 1.0794 0.01673 0.00843 -0.0838 0.3821 1.0002
3.500 1.1016 0.01709 0.00874 -0.0832 0.3745 1.0002
3.750 1.1227 0.01748 0.00908 -0.0825 0.3671 1.0002
4.000 1.1433 0.01789 0.00944 -0.0818 0.3608 1.0002
4.250 1.1642 0.01828 0.00982 -0.0811 0.3547 1.0002
4.500 1.1838 0.01873 0.01022 -0.0802 0.3495 1.0002
4.750 1.2027 0.01919 0.01063 -0.0793 0.3447 1.0002
5.000 1.2219 0.01962 0.01108 -0.0784 0.3393 1.0002
5.250 1.2375 0.02012 0.01156 -0.0769 0.3338 1.0002
5.500 1.2514 0.02071 0.01208 -0.0753 0.3289 1.0002
5.750 1.2683 0.02121 0.01261 -0.0741 0.3241 1.0002
6.000 1.2844 0.02176 0.01318 -0.0729 0.3192 1.0002
6.250 1.2994 0.02239 0.01379 -0.0717 0.3145 1.0002
6.500 1.3149 0.02306 0.01441 -0.0706 0.3102 1.0002
6.750 1.3315 0.02365 0.01507 -0.0697 0.3056 1.0002
7.000 1.3471 0.02431 0.01577 -0.0687 0.3011 1.0002
7.250 1.3620 0.02504 0.01649 -0.0677 0.2970 1.0002
7.500 1.3772 0.02580 0.01721 -0.0668 0.2935 1.0002
7.750 1.3934 0.02649 0.01799 -0.0661 0.2900 1.0002
8.000 1.4088 0.02725 0.01882 -0.0653 0.2861 1.0002
8.250 1.4231 0.02808 0.01969 -0.0645 0.2823 1.0002
8.500 1.4369 0.02895 0.02057 -0.0636 0.2789 1.0002
8.750 1.4507 0.02986 0.02146 -0.0629 0.2758 1.0002
9.000 1.4650 0.03076 0.02249 -0.0622 0.2723 1.0002
9.250 1.4781 0.03173 0.02355 -0.0615 0.2686 1.0002
9.500 1.4902 0.03279 0.02466 -0.0608 0.2649 1.0002
9.750 1.5013 0.03393 0.02581 -0.0600 0.2615 1.0002
10.000 1.5126 0.03507 0.02700 -0.0593 0.2582 1.0002
10.250 1.5236 0.03630 0.02835 -0.0587 0.2543 1.0002
10.500 1.5333 0.03762 0.02975 -0.0581 0.2502 1.0002
10.750 1.5418 0.03905 0.03123 -0.0574 0.2463 1.0002
11.000 1.5491 0.04056 0.03274 -0.0567 0.2427 1.0002
11.250 1.5573 0.04214 0.03447 -0.0563 0.2382 1.0002
11.500 1.5634 0.04392 0.03633 -0.0558 0.2335 1.0002
11.750 1.5681 0.04583 0.03828 -0.0553 0.2290 1.0002
12.000 1.5736 0.04776 0.04029 -0.0549 0.2247 1.0002
12.250 1.5782 0.04986 0.04250 -0.0546 0.2197 1.0002
12.500 1.5804 0.05219 0.04488 -0.0543 0.2149 1.0002
12.750 1.5825 0.05460 0.04734 -0.0541 0.2101 1.0002
13.000 1.5839 0.05720 0.05006 -0.0540 0.2043 1.0002
13.250 1.5819 0.06016 0.05304 -0.0539 0.1987 1.0002
13.500 1.5808 0.06314 0.05610 -0.0539 0.1928 1.0002
13.750 1.5768 0.06649 0.05950 -0.0540 0.1866 1.0002
14.000 1.5721 0.06998 0.06303 -0.0542 0.1807 1.0002
14.250 1.5667 0.07364 0.06676 -0.0544 0.1743 1.0002
14.500 1.5594 0.07753 0.07066 -0.0547 0.1687 1.0002
14.750 1.5537 0.08134 0.07455 -0.0552 0.1630 1.0002
15.000 1.5454 0.08550 0.07874 -0.0557 0.1580 1.0002
15.250 1.5396 0.08938 0.08269 -0.0563 0.1535 1.0002
15.500 1.5333 0.09336 0.08674 -0.0569 0.1490 1.0002
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Polar data table (+)
Polar graphs
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