NASA/LANGLEY LS(1)-0413 (GA(W)-2) AIRFOIL (ls413-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY LS(1)-0413 (GA(W)-2) AIRFOIL (ls413-il) Reynolds number: 50,000 Max Cl/Cd: 33.79 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ls413-il-50000-n5.txt Download as CSV file: xf-ls413-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY LS(1)-0413 (GA(W)-2) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4484 0.10255 0.09480 -0.0499 1.0000 0.0657
-10.500 -0.4580 0.09715 0.08948 -0.0522 1.0000 0.0643
-10.000 -0.5493 0.08005 0.07244 -0.0616 1.0000 0.0598
-9.750 -0.5707 0.07735 0.06981 -0.0597 1.0000 0.0596
-9.500 -0.5901 0.07437 0.06684 -0.0582 1.0000 0.0593
-9.250 -0.6075 0.07138 0.06380 -0.0564 1.0000 0.0590
-9.000 -0.6221 0.06827 0.06059 -0.0548 1.0000 0.0588
-8.750 -0.6327 0.06507 0.05723 -0.0533 1.0000 0.0586
-8.500 -0.6389 0.06177 0.05371 -0.0521 1.0000 0.0584
-8.250 -0.6405 0.05845 0.05012 -0.0512 1.0000 0.0582
-8.000 -0.6376 0.05519 0.04653 -0.0506 1.0000 0.0583
-7.750 -0.6304 0.05204 0.04298 -0.0502 1.0000 0.0588
-7.500 -0.6191 0.04909 0.03955 -0.0500 1.0000 0.0596
-7.250 -0.6044 0.04642 0.03652 -0.0499 1.0000 0.0605
-7.000 -0.5876 0.04422 0.03416 -0.0496 1.0000 0.0615
-6.750 -0.5690 0.04221 0.03191 -0.0493 1.0000 0.0624
-6.500 -0.5488 0.04027 0.02971 -0.0490 1.0000 0.0632
-6.250 -0.5274 0.03854 0.02772 -0.0487 1.0000 0.0642
-6.000 -0.5017 0.03692 0.02585 -0.0490 0.9989 0.0655
-5.750 -0.4706 0.03549 0.02414 -0.0501 0.9960 0.0681
-5.500 -0.4386 0.03433 0.02265 -0.0510 0.9932 0.0715
-5.250 -0.4105 0.03318 0.02157 -0.0514 0.9901 0.0748
-5.000 -0.3816 0.03230 0.02061 -0.0517 0.9870 0.0783
-4.750 -0.3518 0.03162 0.01972 -0.0520 0.9843 0.0837
-4.500 -0.3226 0.03080 0.01899 -0.0528 0.9816 0.0908
-4.250 -0.2941 0.03006 0.01817 -0.0534 0.9780 0.0991
-4.000 -0.2628 0.02924 0.01740 -0.0550 0.9746 0.1140
-3.750 -0.2288 0.02817 0.01656 -0.0574 0.9717 0.1450
-3.250 -0.1788 0.02621 0.01727 -0.0567 0.9655 0.6070
-3.000 -0.1578 0.02710 0.01809 -0.0541 0.9601 0.6862
-2.750 -0.1486 0.02839 0.01943 -0.0472 0.9551 0.7507
-2.500 -0.1448 0.02900 0.02001 -0.0403 0.9489 0.7911
-2.250 -0.1268 0.02921 0.02008 -0.0374 0.9441 0.8151
-2.000 -0.0980 0.02929 0.01995 -0.0376 0.9405 0.8300
-1.750 -0.0787 0.02928 0.01979 -0.0362 0.9348 0.8444
-1.500 -0.0534 0.02929 0.01965 -0.0360 0.9298 0.8583
-1.250 -0.0235 0.02931 0.01952 -0.0366 0.9257 0.8699
-1.000 -0.0013 0.02928 0.01938 -0.0360 0.9199 0.8805
-0.750 0.0249 0.02929 0.01929 -0.0362 0.9143 0.8914
-0.500 0.0574 0.02936 0.01925 -0.0377 0.9100 0.9015
-0.250 0.0813 0.02938 0.01920 -0.0376 0.9040 0.9106
0.000 0.1096 0.02946 0.01923 -0.0385 0.8980 0.9192
0.250 0.1447 0.02957 0.01927 -0.0405 0.8934 0.9268
0.500 0.1692 0.02971 0.01937 -0.0407 0.8864 0.9348
0.750 0.2009 0.02986 0.01950 -0.0423 0.8803 0.9428
1.000 0.2387 0.03001 0.01964 -0.0448 0.8752 0.9500
1.250 0.2648 0.03019 0.01984 -0.0454 0.8659 0.9589
1.500 0.3081 0.03030 0.01996 -0.0488 0.8601 0.9662
1.750 0.3358 0.03050 0.02021 -0.0497 0.8494 0.9765
2.000 0.3741 0.03060 0.02035 -0.0522 0.8416 0.9892
2.250 0.4026 0.03075 0.02056 -0.0531 0.8311 1.0000
2.500 0.4334 0.03099 0.02086 -0.0544 0.8208 1.0000
2.750 0.4779 0.03085 0.02079 -0.0572 0.8120 1.0000
3.000 0.5083 0.03088 0.02091 -0.0580 0.7982 1.0000
3.250 0.5412 0.03080 0.02092 -0.0589 0.7844 1.0000
3.500 0.5771 0.03044 0.02067 -0.0599 0.7695 1.0000
3.750 0.6149 0.02974 0.02009 -0.0606 0.7525 1.0000
4.000 0.6520 0.02896 0.01943 -0.0611 0.7348 1.0000
4.250 0.6882 0.02823 0.01884 -0.0614 0.7165 1.0000
4.500 0.7137 0.02787 0.01862 -0.0605 0.6930 1.0000
4.750 0.7458 0.02711 0.01798 -0.0600 0.6674 1.0000
5.000 0.7679 0.02688 0.01787 -0.0586 0.6332 1.0000
5.250 0.7927 0.02658 0.01765 -0.0574 0.5896 1.0000
5.500 0.8316 0.02563 0.01652 -0.0572 0.5250 1.0000
5.750 0.8646 0.02559 0.01591 -0.0566 0.4367 1.0000
6.000 0.8810 0.02665 0.01644 -0.0549 0.3677 1.0000
6.250 0.8940 0.02797 0.01738 -0.0532 0.3170 1.0000
6.500 0.9082 0.02937 0.01845 -0.0519 0.2806 1.0000
6.750 0.9254 0.03068 0.01961 -0.0510 0.2511 1.0000
7.000 0.9444 0.03194 0.02073 -0.0504 0.2289 1.0000
7.250 0.9654 0.03315 0.02186 -0.0500 0.2102 1.0000
7.500 0.9881 0.03433 0.02299 -0.0498 0.1949 1.0000
7.750 1.0136 0.03548 0.02409 -0.0498 0.1822 1.0000
8.000 1.0406 0.03663 0.02519 -0.0501 0.1704 1.0000
8.250 1.0702 0.03781 0.02649 -0.0507 0.1596 1.0000
8.500 1.1004 0.03912 0.02783 -0.0514 0.1506 1.0000
8.750 1.1277 0.04047 0.02926 -0.0518 0.1421 1.0000
9.000 1.1570 0.04204 0.03096 -0.0524 0.1348 1.0000
9.250 1.1804 0.04356 0.03262 -0.0524 0.1280 1.0000
9.500 1.2048 0.04526 0.03438 -0.0525 0.1223 1.0000
9.750 1.2243 0.04715 0.03657 -0.0519 0.1168 1.0000
10.000 1.2443 0.04879 0.03824 -0.0516 0.1120 1.0000
10.250 1.2605 0.05096 0.04068 -0.0507 0.1078 1.0000
10.500 1.2705 0.05331 0.04339 -0.0492 0.1039 1.0000
10.750 1.2808 0.05535 0.04561 -0.0477 0.1004 1.0000
11.000 1.2985 0.05722 0.04743 -0.0473 0.0970 1.0000
11.250 1.2941 0.06022 0.05087 -0.0445 0.0947 1.0000
11.500 1.2873 0.06350 0.05458 -0.0420 0.0927 1.0000
11.750 1.2790 0.06686 0.05828 -0.0397 0.0908 1.0000
12.000 1.2698 0.07029 0.06198 -0.0379 0.0890 1.0000
12.250 1.2609 0.07373 0.06565 -0.0365 0.0874 1.0000
12.500 1.2568 0.07687 0.06892 -0.0355 0.0857 1.0000
12.750 1.2623 0.07957 0.07161 -0.0350 0.0839 1.0000
13.000 1.2318 0.08537 0.07778 -0.0346 0.0835 1.0000
13.250 1.1981 0.09222 0.08493 -0.0356 0.0834 1.0000
13.500 1.1600 0.10054 0.09352 -0.0385 0.0834 1.0000
13.750 1.1166 0.11115 0.10436 -0.0440 0.0837 1.0000
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Polar data table (+)
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