NACA 4415 (naca4415-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 4415 (naca4415-il) Reynolds number: 100,000 Max Cl/Cd: 50.7 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca4415-il-100000-n5.txt Download as CSV file: xf-naca4415-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 4415
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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.6540 0.05863 0.05283 -0.0780 1.0000 0.0386
-11.250 -0.6883 0.05473 0.04886 -0.0776 1.0000 0.0383
-11.000 -0.7241 0.05230 0.04637 -0.0739 1.0000 0.0382
-10.750 -0.7502 0.04908 0.04288 -0.0718 0.9966 0.0383
-10.500 -0.7437 0.04577 0.03930 -0.0736 0.9896 0.0390
-10.250 -0.7265 0.04365 0.03705 -0.0750 0.9839 0.0399
-10.000 -0.7127 0.04145 0.03464 -0.0756 0.9771 0.0410
-9.750 -0.6954 0.03891 0.03175 -0.0768 0.9715 0.0427
-9.500 -0.6811 0.03701 0.02961 -0.0764 0.9641 0.0444
-9.250 -0.6560 0.03577 0.02829 -0.0774 0.9592 0.0464
-9.000 -0.6391 0.03412 0.02635 -0.0769 0.9522 0.0486
-8.750 -0.6154 0.03279 0.02490 -0.0773 0.9467 0.0507
-8.500 -0.5904 0.03166 0.02364 -0.0777 0.9416 0.0536
-8.250 -0.5705 0.03056 0.02237 -0.0770 0.9342 0.0568
-8.000 -0.5409 0.02960 0.02130 -0.0781 0.9299 0.0608
-7.750 -0.5211 0.02875 0.02034 -0.0771 0.9224 0.0646
-7.500 -0.4943 0.02788 0.01930 -0.0773 0.9167 0.0699
-7.250 -0.4617 0.02711 0.01850 -0.0787 0.9131 0.0757
-7.000 -0.4443 0.02647 0.01775 -0.0770 0.9042 0.0810
-6.750 -0.4139 0.02577 0.01690 -0.0777 0.8993 0.0886
-6.500 -0.3795 0.02511 0.01623 -0.0792 0.8961 0.0965
-6.250 -0.3632 0.02468 0.01574 -0.0771 0.8862 0.1028
-6.000 -0.3304 0.02408 0.01498 -0.0780 0.8819 0.1121
-5.750 -0.2994 0.02357 0.01447 -0.0787 0.8773 0.1204
-5.500 -0.2786 0.02318 0.01402 -0.0774 0.8685 0.1280
-5.250 -0.2440 0.02269 0.01339 -0.0786 0.8644 0.1387
-5.000 -0.2180 0.02229 0.01303 -0.0782 0.8577 0.1471
-4.750 -0.1911 0.02187 0.01255 -0.0779 0.8505 0.1564
-4.500 -0.1547 0.02137 0.01198 -0.0794 0.8465 0.1674
-4.250 -0.1320 0.02102 0.01165 -0.0784 0.8381 0.1756
-4.000 -0.1004 0.02061 0.01115 -0.0789 0.8319 0.1868
-3.750 -0.0620 0.02009 0.01065 -0.0808 0.8280 0.1989
-3.500 -0.0428 0.01985 0.01042 -0.0790 0.8180 0.2086
-3.250 -0.0076 0.01943 0.00997 -0.0802 0.8124 0.2226
-3.000 0.0199 0.01915 0.00967 -0.0799 0.8048 0.2366
-2.750 0.0480 0.01883 0.00939 -0.0798 0.7968 0.2514
-2.500 0.0866 0.01840 0.00895 -0.0816 0.7920 0.2711
-2.250 0.1048 0.01826 0.00886 -0.0796 0.7809 0.2869
-2.000 0.1416 0.01787 0.00848 -0.0810 0.7750 0.3105
-1.750 0.1620 0.01772 0.00838 -0.0795 0.7643 0.3317
-1.500 0.1966 0.01733 0.00808 -0.0805 0.7577 0.3616
-1.250 0.2181 0.01717 0.00800 -0.0792 0.7472 0.3921
-1.000 0.2518 0.01677 0.00776 -0.0800 0.7399 0.4400
-0.750 0.2736 0.01656 0.00777 -0.0787 0.7295 0.4976
-0.500 0.3071 0.01613 0.00763 -0.0794 0.7220 0.5904
-0.250 0.3302 0.01593 0.00772 -0.0780 0.7114 0.6830
0.000 0.3826 0.01562 0.00769 -0.0820 0.7041 0.7993
0.250 0.4602 0.01568 0.00783 -0.0916 0.6933 0.8954
0.500 0.5273 0.01572 0.00774 -0.0992 0.6844 0.9424
0.750 0.5734 0.01588 0.00781 -0.1028 0.6733 0.9759
1.000 0.6255 0.01602 0.00781 -0.1078 0.6633 0.9994
1.250 0.6470 0.01610 0.00778 -0.1067 0.6534 1.0000
1.500 0.6658 0.01623 0.00781 -0.1049 0.6436 1.0000
1.750 0.6880 0.01634 0.00780 -0.1038 0.6345 1.0000
2.000 0.7061 0.01651 0.00791 -0.1019 0.6247 1.0000
2.250 0.7295 0.01664 0.00791 -0.1009 0.6161 1.0000
2.500 0.7471 0.01684 0.00808 -0.0990 0.6063 1.0000
2.750 0.7709 0.01699 0.00812 -0.0981 0.5980 1.0000
3.000 0.7882 0.01722 0.00832 -0.0960 0.5884 1.0000
3.250 0.8120 0.01740 0.00839 -0.0951 0.5804 1.0000
3.500 0.8291 0.01765 0.00863 -0.0931 0.5709 1.0000
3.750 0.8526 0.01784 0.00873 -0.0921 0.5628 1.0000
4.000 0.8697 0.01811 0.00900 -0.0900 0.5535 1.0000
4.250 0.8925 0.01832 0.00913 -0.0890 0.5454 1.0000
4.500 0.9094 0.01860 0.00943 -0.0869 0.5361 1.0000
4.750 0.9315 0.01882 0.00958 -0.0857 0.5279 1.0000
5.000 0.9482 0.01912 0.00990 -0.0836 0.5188 1.0000
5.250 0.9694 0.01937 0.01009 -0.0822 0.5105 1.0000
5.500 0.9854 0.01968 0.01043 -0.0800 0.5012 1.0000
5.750 1.0059 0.01993 0.01062 -0.0785 0.4926 1.0000
6.000 1.0200 0.02025 0.01098 -0.0760 0.4824 1.0000
6.250 1.0393 0.02050 0.01117 -0.0743 0.4731 1.0000
6.500 1.0516 0.02083 0.01155 -0.0714 0.4625 1.0000
6.750 1.0681 0.02114 0.01183 -0.0693 0.4530 1.0000
7.000 1.0818 0.02148 0.01219 -0.0667 0.4431 1.0000
7.250 1.0950 0.02182 0.01255 -0.0641 0.4337 1.0000
7.500 1.1085 0.02216 0.01289 -0.0615 0.4245 1.0000
7.750 1.1199 0.02256 0.01333 -0.0586 0.4148 1.0000
8.000 1.1340 0.02292 0.01366 -0.0562 0.4055 1.0000
8.250 1.1440 0.02339 0.01421 -0.0533 0.3952 1.0000
8.500 1.1568 0.02383 0.01463 -0.0508 0.3857 1.0000
8.750 1.1671 0.02434 0.01519 -0.0481 0.3752 1.0000
9.000 1.1778 0.02489 0.01578 -0.0455 0.3649 1.0000
9.250 1.1889 0.02544 0.01629 -0.0430 0.3547 1.0000
9.500 1.1976 0.02611 0.01705 -0.0403 0.3435 1.0000
9.750 1.2068 0.02681 0.01775 -0.0377 0.3329 1.0000
10.000 1.2157 0.02754 0.01849 -0.0353 0.3224 1.0000
10.250 1.2226 0.02841 0.01941 -0.0327 0.3108 1.0000
10.500 1.2300 0.02931 0.02033 -0.0303 0.2999 1.0000
10.750 1.2367 0.03027 0.02127 -0.0279 0.2894 1.0000
11.000 1.2426 0.03137 0.02243 -0.0257 0.2782 1.0000
11.250 1.2479 0.03253 0.02361 -0.0235 0.2678 1.0000
11.500 1.2525 0.03379 0.02483 -0.0213 0.2577 1.0000
11.750 1.2569 0.03516 0.02627 -0.0194 0.2473 1.0000
12.000 1.2600 0.03664 0.02775 -0.0174 0.2374 1.0000
12.250 1.2622 0.03824 0.02935 -0.0156 0.2276 1.0000
12.500 1.2645 0.03995 0.03112 -0.0139 0.2180 1.0000
12.750 1.2657 0.04175 0.03289 -0.0124 0.2095 1.0000
13.000 1.2670 0.04369 0.03491 -0.0110 0.2005 1.0000
13.250 1.2684 0.04566 0.03688 -0.0098 0.1930 1.0000
13.500 1.2694 0.04777 0.03907 -0.0087 0.1853 1.0000
13.750 1.2703 0.04993 0.04124 -0.0077 0.1787 1.0000
14.000 1.2712 0.05221 0.04363 -0.0070 0.1718 1.0000
14.250 1.2709 0.05458 0.04597 -0.0062 0.1658 1.0000
14.500 1.2715 0.05708 0.04862 -0.0057 0.1593 1.0000
14.750 1.2704 0.05970 0.05125 -0.0053 0.1536 1.0000
15.000 1.2698 0.06242 0.05406 -0.0050 0.1478 1.0000
15.250 1.2681 0.06531 0.05704 -0.0049 0.1423 1.0000
15.500 1.2664 0.06822 0.05997 -0.0048 0.1371 1.0000
15.750 1.2640 0.07139 0.06329 -0.0049 0.1317 1.0000
16.000 1.2608 0.07460 0.06653 -0.0052 0.1268 1.0000
16.250 1.2575 0.07800 0.07004 -0.0055 0.1217 1.0000
16.500 1.2532 0.08159 0.07373 -0.0061 0.1168 1.0000
16.750 1.2503 0.08492 0.07704 -0.0066 0.1126 1.0000
17.000 1.2447 0.08890 0.08122 -0.0074 0.1077 1.0000
17.250 1.2394 0.09277 0.08515 -0.0083 0.1035 1.0000
17.500 1.2347 0.09661 0.08905 -0.0093 0.0995 1.0000
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Polar data table (+)
Polar graphs
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