NASA/LANGLEY LS(1)-0413 (GA(W)-2) AIRFOIL (ls413-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY LS(1)-0413 (GA(W)-2) AIRFOIL (ls413-il) Reynolds number: 100,000 Max Cl/Cd: 53.04 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ls413-il-100000.txt Download as CSV file: xf-ls413-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4516 0.09762 0.09264 -0.0421 1.0000 0.1572
-9.250 -0.3810 0.09551 0.09101 -0.0312 1.0000 0.1637
-9.000 -0.4534 0.09266 0.08780 -0.0373 1.0000 0.1645
-8.750 -0.4675 0.09091 0.08614 -0.0347 1.0000 0.1693
-8.500 -0.5127 0.08902 0.08440 -0.0323 1.0000 0.1723
-8.250 -0.5731 0.08555 0.08107 -0.0329 1.0000 0.1735
-8.000 -0.5858 0.08176 0.07733 -0.0317 1.0000 0.1770
-7.750 -0.5597 0.08184 0.07745 -0.0253 1.0000 0.1836
-7.500 -0.6229 0.07492 0.07040 -0.0329 1.0000 0.1920
-7.250 -0.5944 0.07442 0.07009 -0.0264 1.0000 0.1970
-6.500 -0.5794 0.04394 0.03687 -0.0475 1.0000 0.0957
-6.250 -0.5494 0.03988 0.03184 -0.0488 1.0000 0.0837
-6.000 -0.5246 0.03655 0.02836 -0.0496 1.0000 0.0817
-5.750 -0.4983 0.03419 0.02569 -0.0501 1.0000 0.0801
-5.500 -0.4715 0.03227 0.02345 -0.0505 1.0000 0.0792
-5.250 -0.4450 0.03073 0.02164 -0.0507 1.0000 0.0793
-5.000 -0.4191 0.02964 0.02032 -0.0507 1.0000 0.0813
-4.750 -0.3932 0.02881 0.01923 -0.0506 1.0000 0.0833
-4.500 -0.3672 0.02751 0.01789 -0.0506 1.0000 0.0852
-4.250 -0.3415 0.02651 0.01699 -0.0506 1.0000 0.0881
-4.000 -0.3156 0.02585 0.01635 -0.0506 1.0000 0.0925
-3.750 -0.2886 0.02522 0.01574 -0.0509 1.0000 0.0997
-3.500 -0.2549 0.02465 0.01528 -0.0526 0.9986 0.1112
-3.250 -0.2120 0.02387 0.01475 -0.0564 0.9962 0.1393
-3.000 -0.1679 0.02234 0.01598 -0.0592 0.9953 0.6795
-2.750 -0.1498 0.02352 0.01715 -0.0555 0.9904 0.7233
-2.500 -0.1308 0.02448 0.01806 -0.0524 0.9855 0.7532
-2.250 -0.1118 0.02535 0.01888 -0.0493 0.9810 0.7811
-2.000 -0.1076 0.02602 0.01957 -0.0427 0.9754 0.8126
-1.750 -0.1033 0.02653 0.02009 -0.0356 0.9705 0.8467
-1.500 -0.0991 0.02657 0.02011 -0.0298 0.9649 0.8747
-1.250 -0.0810 0.02653 0.01999 -0.0276 0.9596 0.8921
-1.000 -0.0441 0.02680 0.02013 -0.0300 0.9553 0.9031
-0.750 -0.0300 0.02662 0.01990 -0.0278 0.9487 0.9159
-0.500 -0.0043 0.02661 0.01981 -0.0278 0.9434 0.9290
-0.250 0.0246 0.02670 0.01983 -0.0286 0.9380 0.9393
0.000 0.0511 0.02669 0.01977 -0.0292 0.9302 0.9495
0.250 0.0956 0.02695 0.01995 -0.0328 0.9247 0.9597
0.500 0.1197 0.02693 0.01991 -0.0332 0.9149 0.9695
0.750 0.1714 0.02723 0.02016 -0.0383 0.9089 0.9766
1.000 0.2013 0.02740 0.02033 -0.0399 0.8985 0.9848
1.500 0.2775 0.02786 0.02079 -0.0457 0.8809 1.0000
1.750 0.3165 0.02804 0.02098 -0.0484 0.8710 1.0000
2.000 0.3653 0.02799 0.02094 -0.0524 0.8615 1.0000
2.250 0.3980 0.02807 0.02105 -0.0539 0.8490 1.0000
2.500 0.4404 0.02793 0.02096 -0.0566 0.8377 1.0000
2.750 0.5068 0.02680 0.01987 -0.0617 0.8281 1.0000
3.000 0.5452 0.02625 0.01939 -0.0631 0.8139 1.0000
3.250 0.5848 0.02568 0.01890 -0.0646 0.8010 1.0000
3.500 0.6562 0.02355 0.01687 -0.0694 0.7950 1.0000
3.750 0.6949 0.02251 0.01592 -0.0701 0.7806 1.0000
4.000 0.7341 0.02141 0.01493 -0.0707 0.7660 1.0000
4.250 0.7740 0.02024 0.01386 -0.0714 0.7501 1.0000
4.500 0.8152 0.01897 0.01268 -0.0721 0.7315 1.0000
4.750 0.8432 0.01830 0.01212 -0.0712 0.7037 1.0000
5.000 0.8753 0.01747 0.01132 -0.0708 0.6654 1.0000
5.250 0.9016 0.01700 0.01075 -0.0694 0.5924 1.0000
5.500 0.9224 0.01753 0.01026 -0.0671 0.4442 1.0000
5.750 0.9317 0.01927 0.01113 -0.0645 0.3392 1.0000
6.000 0.9473 0.02085 0.01215 -0.0632 0.2828 1.0000
6.250 0.9688 0.02224 0.01319 -0.0629 0.2483 1.0000
6.500 0.9937 0.02340 0.01420 -0.0631 0.2234 1.0000
6.750 1.0206 0.02460 0.01523 -0.0636 0.2055 1.0000
7.000 1.0489 0.02580 0.01634 -0.0643 0.1907 1.0000
7.250 1.0786 0.02706 0.01755 -0.0652 0.1785 1.0000
7.500 1.1101 0.02848 0.01882 -0.0664 0.1680 1.0000
7.750 1.1382 0.02966 0.02007 -0.0670 0.1583 1.0000
8.000 1.1691 0.03122 0.02166 -0.0680 0.1501 1.0000
8.250 1.1968 0.03252 0.02298 -0.0686 0.1422 1.0000
8.500 1.2258 0.03430 0.02487 -0.0693 0.1355 1.0000
8.750 1.2502 0.03567 0.02639 -0.0692 0.1290 1.0000
9.000 1.2788 0.03771 0.02839 -0.0701 0.1232 1.0000
9.250 1.2982 0.03936 0.03041 -0.0691 0.1181 1.0000
9.500 1.3211 0.04090 0.03201 -0.0689 0.1131 1.0000
9.750 1.3427 0.04347 0.03473 -0.0688 0.1089 1.0000
10.000 1.3542 0.04567 0.03738 -0.0667 0.1053 1.0000
10.250 1.3705 0.04762 0.03952 -0.0656 0.1015 1.0000
10.500 1.3914 0.04973 0.04161 -0.0655 0.0980 1.0000
10.750 1.3984 0.05330 0.04553 -0.0636 0.0959 1.0000
11.000 1.3934 0.05634 0.04908 -0.0599 0.0944 1.0000
11.250 1.3849 0.05965 0.05284 -0.0561 0.0930 1.0000
11.500 1.3714 0.06296 0.05650 -0.0520 0.0918 1.0000
11.750 1.3528 0.06637 0.06022 -0.0478 0.0910 1.0000
12.000 1.3304 0.07023 0.06439 -0.0442 0.0905 1.0000
12.250 1.3021 0.07489 0.06934 -0.0412 0.0904 1.0000
12.500 1.2663 0.08065 0.07541 -0.0394 0.0909 1.0000
12.750 1.2236 0.08789 0.08292 -0.0393 0.0918 1.0000
13.000 1.1773 0.09681 0.09206 -0.0415 0.0932 1.0000
13.250 1.1337 0.10717 0.10258 -0.0459 0.0947 1.0000
13.500 1.0995 0.11802 0.11353 -0.0514 0.0959 1.0000
13.750 1.0805 0.12761 0.12315 -0.0558 0.0967 1.0000
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Polar data table (+)
Polar graphs
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