N-24 (n24-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: N-24 (n24-il) Reynolds number: 100,000 Max Cl/Cd: 47.01 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n24-il-100000-n5.txt Download as CSV file: xf-n24-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.2148 0.09902 0.09374 -0.0608 0.9031 0.0530
-12.250 -0.2206 0.09405 0.08876 -0.0631 0.8957 0.0528
-11.750 -0.4098 0.05050 0.04457 -0.0984 0.8732 0.0516
-11.500 -0.4134 0.04714 0.04096 -0.0984 0.8654 0.0521
-11.250 -0.4100 0.04427 0.03782 -0.0983 0.8575 0.0526
-11.000 -0.4036 0.04153 0.03478 -0.0977 0.8495 0.0533
-10.750 -0.3950 0.03892 0.03182 -0.0966 0.8439 0.0539
-10.500 -0.3815 0.03653 0.02909 -0.0961 0.8354 0.0547
-10.250 -0.3664 0.03434 0.02652 -0.0951 0.8288 0.0556
-10.000 -0.3497 0.03228 0.02403 -0.0937 0.8237 0.0567
-9.750 -0.3267 0.03148 0.02320 -0.0932 0.8150 0.0576
-9.500 -0.3048 0.03053 0.02212 -0.0922 0.8086 0.0587
-9.250 -0.2825 0.02947 0.02086 -0.0912 0.8028 0.0603
-9.000 -0.2590 0.02832 0.01943 -0.0906 0.7947 0.0628
-8.750 -0.2349 0.02772 0.01879 -0.0898 0.7889 0.0648
-8.500 -0.2104 0.02691 0.01778 -0.0890 0.7825 0.0680
-8.250 -0.1854 0.02617 0.01695 -0.0885 0.7746 0.0711
-8.000 -0.1606 0.02538 0.01599 -0.0875 0.7688 0.0753
-7.750 -0.1351 0.02472 0.01528 -0.0871 0.7613 0.0798
-7.500 -0.1093 0.02408 0.01450 -0.0865 0.7542 0.0858
-7.250 -0.0836 0.02355 0.01394 -0.0858 0.7490 0.0917
-7.000 -0.0569 0.02322 0.01358 -0.0856 0.7410 0.0981
-6.750 -0.0300 0.02286 0.01312 -0.0852 0.7341 0.1049
-6.500 -0.0033 0.02254 0.01276 -0.0845 0.7289 0.1110
-6.250 0.0242 0.02239 0.01257 -0.0845 0.7202 0.1179
-6.000 0.0516 0.02218 0.01228 -0.0842 0.7142 0.1252
-5.750 0.0791 0.02193 0.01198 -0.0838 0.7086 0.1316
-5.500 0.1067 0.02182 0.01182 -0.0838 0.7006 0.1394
-5.250 0.1342 0.02156 0.01154 -0.0834 0.6946 0.1469
-5.000 0.1620 0.02136 0.01126 -0.0832 0.6884 0.1550
-4.750 0.1893 0.02112 0.01106 -0.0831 0.6811 0.1616
-4.500 0.2169 0.02080 0.01067 -0.0827 0.6750 0.1692
-4.250 0.2440 0.02055 0.01043 -0.0824 0.6664 0.1779
-4.000 0.2714 0.02027 0.01009 -0.0820 0.6579 0.1899
-3.750 0.2985 0.02002 0.00987 -0.0817 0.6492 0.2042
-3.500 0.3258 0.01981 0.00968 -0.0815 0.6407 0.2217
-3.250 0.3538 0.01960 0.00945 -0.0812 0.6347 0.2424
-3.000 0.3810 0.01954 0.00947 -0.0812 0.6265 0.2660
-2.750 0.4089 0.01937 0.00933 -0.0811 0.6201 0.2942
-2.500 0.4368 0.01925 0.00928 -0.0811 0.6135 0.3299
-2.250 0.4643 0.01912 0.00933 -0.0811 0.6059 0.3808
-2.000 0.4919 0.01883 0.00924 -0.0810 0.6000 0.4574
-1.750 0.5168 0.01852 0.00938 -0.0804 0.5928 0.5764
-1.500 0.5849 0.01772 0.00944 -0.0876 0.5844 0.9940
-1.250 0.6145 0.01785 0.00937 -0.0880 0.5779 1.0002
-1.000 0.6399 0.01807 0.00949 -0.0877 0.5698 1.0002
-0.750 0.6664 0.01819 0.00943 -0.0874 0.5632 1.0002
-0.500 0.6920 0.01842 0.00955 -0.0871 0.5559 1.0002
-0.250 0.7177 0.01863 0.00965 -0.0869 0.5483 1.0002
0.000 0.7444 0.01876 0.00961 -0.0866 0.5418 1.0002
0.250 0.7688 0.01906 0.00988 -0.0863 0.5329 1.0002
0.500 0.7949 0.01923 0.00991 -0.0860 0.5256 1.0002
0.750 0.8196 0.01951 0.01013 -0.0857 0.5174 1.0002
1.000 0.8446 0.01975 0.01029 -0.0854 0.5095 1.0002
1.250 0.8701 0.01999 0.01042 -0.0852 0.5022 1.0002
1.500 0.8937 0.02030 0.01071 -0.0847 0.4931 1.0002
1.750 0.9193 0.02051 0.01078 -0.0845 0.4858 1.0002
2.000 0.9415 0.02089 0.01118 -0.0839 0.4760 1.0002
2.250 0.9663 0.02112 0.01129 -0.0836 0.4685 1.0002
2.500 0.9881 0.02153 0.01172 -0.0830 0.4593 1.0002
2.750 1.0118 0.02183 0.01193 -0.0826 0.4517 1.0002
3.000 1.0334 0.02224 0.01234 -0.0820 0.4431 1.0002
3.250 1.0557 0.02259 0.01262 -0.0814 0.4351 1.0002
3.500 1.0769 0.02300 0.01301 -0.0807 0.4272 1.0002
3.750 1.0978 0.02342 0.01340 -0.0800 0.4194 1.0002
4.000 1.1197 0.02382 0.01372 -0.0794 0.4130 1.0002
4.250 1.1389 0.02434 0.01427 -0.0786 0.4057 1.0002
4.500 1.1599 0.02476 0.01462 -0.0779 0.3997 1.0002
4.750 1.1791 0.02529 0.01515 -0.0771 0.3933 1.0002
5.000 1.1971 0.02585 0.01571 -0.0761 0.3870 1.0002
5.250 1.2179 0.02630 0.01608 -0.0755 0.3819 1.0002
5.500 1.2356 0.02692 0.01672 -0.0745 0.3766 1.0002
5.750 1.2512 0.02757 0.01740 -0.0733 0.3711 1.0002
6.000 1.2691 0.02811 0.01791 -0.0723 0.3663 1.0002
6.250 1.2883 0.02868 0.01843 -0.0716 0.3619 1.0002
6.500 1.2999 0.02951 0.01935 -0.0699 0.3568 1.0002
6.750 1.3144 0.03025 0.02011 -0.0687 0.3519 1.0002
7.000 1.3343 0.03078 0.02056 -0.0681 0.3471 1.0002
7.250 1.3435 0.03175 0.02161 -0.0664 0.3414 1.0002
7.500 1.3525 0.03272 0.02263 -0.0648 0.3352 1.0002
7.750 1.3700 0.03333 0.02316 -0.0641 0.3297 1.0002
8.000 1.3775 0.03450 0.02440 -0.0625 0.3242 1.0002
8.250 1.3855 0.03568 0.02568 -0.0611 0.3189 1.0002
8.500 1.3998 0.03657 0.02658 -0.0603 0.3145 1.0002
8.750 1.4224 0.03706 0.02699 -0.0602 0.3108 1.0002
9.000 1.4240 0.03875 0.02887 -0.0585 0.3065 1.0002
9.250 1.4303 0.04022 0.03046 -0.0573 0.3021 1.0002
9.500 1.4413 0.04138 0.03167 -0.0565 0.2979 1.0002
9.750 1.4604 0.04202 0.03227 -0.0562 0.2941 1.0002
10.000 1.4602 0.04403 0.03444 -0.0548 0.2897 1.0002
10.250 1.4592 0.04616 0.03674 -0.0535 0.2849 1.0002
10.500 1.4658 0.04771 0.03835 -0.0527 0.2805 1.0002
10.750 1.4832 0.04842 0.03902 -0.0524 0.2766 1.0002
11.000 1.4743 0.05141 0.04221 -0.0512 0.2720 1.0002
11.250 1.4675 0.05433 0.04530 -0.0502 0.2672 1.0002
11.500 1.4718 0.05623 0.04728 -0.0496 0.2629 1.0002
11.750 1.4904 0.05677 0.04777 -0.0495 0.2593 1.0002
12.000 1.4640 0.06202 0.05332 -0.0486 0.2539 1.0002
12.250 1.4536 0.06581 0.05725 -0.0482 0.2488 1.0002
12.500 1.4628 0.06735 0.05881 -0.0481 0.2447 1.0002
12.750 1.4510 0.07153 0.06313 -0.0480 0.2398 1.0002
13.000 1.4194 0.07846 0.07029 -0.0484 0.2334 1.0002
13.250 1.4288 0.08008 0.07192 -0.0485 0.2291 1.0002
13.500 1.3992 0.08719 0.07921 -0.0493 0.2231 1.0002
13.750 1.3673 0.09493 0.08711 -0.0506 0.2162 1.0002
14.000 1.3909 0.09450 0.08665 -0.0505 0.2131 1.0002
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Polar data table (+)
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