NASA/LANGLEY LS(1)-0413MOD AIRFOIL (ls413mod-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY LS(1)-0413MOD AIRFOIL (ls413mod-il) Reynolds number: 50,000 Max Cl/Cd: 35.8 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ls413mod-il-50000-n5.txt Download as CSV file: xf-ls413mod-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY LS(1)-0413MOD 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5277 0.07972 0.07204 -0.0562 1.0000 0.0591
-10.000 -0.5413 0.07569 0.06802 -0.0570 1.0000 0.0588
-9.750 -0.5573 0.07190 0.06422 -0.0574 1.0000 0.0585
-9.500 -0.5712 0.06815 0.06041 -0.0574 1.0000 0.0583
-9.250 -0.5825 0.06456 0.05671 -0.0568 1.0000 0.0580
-9.000 -0.5905 0.06107 0.05304 -0.0561 1.0000 0.0578
-8.750 -0.5948 0.05769 0.04944 -0.0552 1.0000 0.0578
-8.500 -0.5955 0.05443 0.04588 -0.0543 1.0000 0.0580
-8.250 -0.5925 0.05130 0.04240 -0.0534 1.0000 0.0585
-8.000 -0.5856 0.04836 0.03902 -0.0526 1.0000 0.0591
-7.750 -0.5743 0.04583 0.03630 -0.0518 1.0000 0.0600
-7.500 -0.5608 0.04367 0.03398 -0.0511 1.0000 0.0609
-7.250 -0.5454 0.04161 0.03171 -0.0503 1.0000 0.0617
-7.000 -0.5284 0.03960 0.02944 -0.0496 1.0000 0.0624
-6.750 -0.5101 0.03776 0.02736 -0.0489 1.0000 0.0633
-6.500 -0.4908 0.03611 0.02548 -0.0482 1.0000 0.0643
-6.250 -0.4707 0.03465 0.02380 -0.0474 1.0000 0.0657
-6.000 -0.4503 0.03340 0.02234 -0.0465 1.0000 0.0680
-5.750 -0.4293 0.03234 0.02102 -0.0456 1.0000 0.0707
-5.500 -0.4097 0.03133 0.02010 -0.0447 1.0000 0.0737
-5.250 -0.3892 0.03052 0.01925 -0.0436 1.0000 0.0769
-5.000 -0.3549 0.02963 0.01817 -0.0448 0.9949 0.0815
-4.750 -0.3212 0.02873 0.01732 -0.0464 0.9894 0.0892
-4.500 -0.2857 0.02784 0.01641 -0.0484 0.9840 0.1006
-4.250 -0.2506 0.02682 0.01547 -0.0507 0.9780 0.1208
-4.000 -0.2133 0.02529 0.01446 -0.0541 0.9726 0.1842
-3.750 -0.1820 0.02332 0.01460 -0.0560 0.9685 0.4968
-3.500 -0.1630 0.02402 0.01563 -0.0522 0.9594 0.6375
-3.250 -0.1393 0.02483 0.01634 -0.0498 0.9510 0.7028
-3.000 -0.1202 0.02568 0.01710 -0.0460 0.9425 0.7495
-2.750 -0.1028 0.02621 0.01752 -0.0422 0.9334 0.7823
-2.500 -0.0787 0.02651 0.01767 -0.0401 0.9259 0.8085
-2.250 -0.0570 0.02662 0.01762 -0.0384 0.9167 0.8301
-2.000 -0.0272 0.02659 0.01743 -0.0381 0.9097 0.8480
-1.750 -0.0035 0.02653 0.01723 -0.0372 0.9003 0.8633
-1.500 0.0318 0.02641 0.01695 -0.0387 0.8935 0.8760
-1.250 0.0572 0.02629 0.01671 -0.0384 0.8838 0.8873
-1.000 0.0937 0.02611 0.01640 -0.0400 0.8770 0.8981
-0.750 0.1196 0.02602 0.01622 -0.0400 0.8668 0.9091
-0.500 0.1571 0.02583 0.01592 -0.0418 0.8601 0.9186
-0.250 0.1840 0.02574 0.01578 -0.0420 0.8492 0.9281
0.000 0.2243 0.02553 0.01549 -0.0443 0.8428 0.9362
0.250 0.2512 0.02552 0.01544 -0.0447 0.8314 0.9458
0.500 0.2896 0.02539 0.01527 -0.0469 0.8233 0.9531
1.000 0.3597 0.02532 0.01519 -0.0503 0.8031 0.9685
1.250 0.4022 0.02514 0.01500 -0.0530 0.7946 0.9752
1.500 0.4365 0.02516 0.01505 -0.0546 0.7820 0.9837
1.750 0.4747 0.02506 0.01498 -0.0567 0.7699 0.9921
2.000 0.5082 0.02480 0.01473 -0.0575 0.7582 1.0000
2.250 0.5356 0.02467 0.01462 -0.0573 0.7451 1.0000
2.500 0.5604 0.02466 0.01464 -0.0568 0.7302 1.0000
2.750 0.5877 0.02460 0.01461 -0.0567 0.7151 1.0000
3.000 0.6163 0.02452 0.01457 -0.0567 0.6996 1.0000
3.250 0.6457 0.02443 0.01453 -0.0567 0.6834 1.0000
3.500 0.6755 0.02433 0.01446 -0.0568 0.6664 1.0000
3.750 0.7061 0.02417 0.01434 -0.0569 0.6478 1.0000
4.000 0.7335 0.02413 0.01433 -0.0566 0.6255 1.0000
4.250 0.7617 0.02406 0.01428 -0.0563 0.6015 1.0000
4.500 0.7892 0.02408 0.01432 -0.0560 0.5754 1.0000
4.750 0.8176 0.02410 0.01429 -0.0558 0.5485 1.0000
5.000 0.8436 0.02431 0.01448 -0.0554 0.5183 1.0000
5.250 0.8692 0.02460 0.01469 -0.0550 0.4862 1.0000
5.500 0.8938 0.02502 0.01502 -0.0544 0.4528 1.0000
5.750 0.9166 0.02560 0.01545 -0.0538 0.4182 1.0000
6.000 0.9382 0.02634 0.01605 -0.0532 0.3841 1.0000
6.250 0.9587 0.02720 0.01680 -0.0525 0.3521 1.0000
6.500 0.9784 0.02817 0.01761 -0.0518 0.3234 1.0000
6.750 0.9982 0.02921 0.01856 -0.0512 0.2983 1.0000
7.000 1.0179 0.03032 0.01954 -0.0506 0.2774 1.0000
7.250 1.0380 0.03146 0.02059 -0.0500 0.2595 1.0000
7.500 1.0591 0.03260 0.02170 -0.0496 0.2439 1.0000
7.750 1.0808 0.03376 0.02287 -0.0493 0.2298 1.0000
8.000 1.1028 0.03494 0.02412 -0.0490 0.2176 1.0000
8.250 1.1257 0.03614 0.02533 -0.0488 0.2076 1.0000
8.500 1.1484 0.03736 0.02658 -0.0486 0.1983 1.0000
8.750 1.1702 0.03868 0.02803 -0.0483 0.1895 1.0000
9.000 1.1930 0.03995 0.02931 -0.0482 0.1820 1.0000
9.250 1.2151 0.04147 0.03104 -0.0479 0.1753 1.0000
9.500 1.2365 0.04291 0.03259 -0.0476 0.1690 1.0000
9.750 1.2569 0.04449 0.03427 -0.0472 0.1631 1.0000
10.000 1.2723 0.04624 0.03630 -0.0463 0.1571 1.0000
10.250 1.2941 0.04778 0.03785 -0.0461 0.1521 1.0000
10.500 1.3056 0.04990 0.04027 -0.0450 0.1473 1.0000
10.750 1.3117 0.05188 0.04251 -0.0432 0.1422 1.0000
11.000 1.3299 0.05320 0.04375 -0.0426 0.1367 1.0000
11.250 1.3237 0.05585 0.04681 -0.0401 0.1326 1.0000
11.500 1.3206 0.05833 0.04956 -0.0383 0.1280 1.0000
11.750 1.3317 0.05983 0.05103 -0.0373 0.1231 1.0000
12.000 1.3242 0.06298 0.05447 -0.0358 0.1197 1.0000
12.250 1.3081 0.06699 0.05886 -0.0346 0.1168 1.0000
12.500 1.2961 0.07087 0.06300 -0.0340 0.1137 1.0000
12.750 1.2991 0.07326 0.06544 -0.0336 0.1100 1.0000
13.000 1.2932 0.07686 0.06916 -0.0335 0.1072 1.0000
13.250 1.2596 0.08395 0.07663 -0.0350 0.1062 1.0000
13.500 1.2184 0.09303 0.08603 -0.0385 0.1057 1.0000
13.750 1.1610 0.10632 0.09960 -0.0456 0.1062 1.0000
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Polar data table (+)
Polar graphs
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