NASA/LANGLEY LS(1)-0413MOD AIRFOIL (ls413mod-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY LS(1)-0413MOD AIRFOIL (ls413mod-il) Reynolds number: 200,000 Max Cl/Cd: 66.01 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ls413mod-il-200000.txt Download as CSV file: xf-ls413mod-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4473 0.08850 0.08481 -0.0413 1.0000 0.0764
-9.750 -0.4547 0.08335 0.07971 -0.0448 1.0000 0.0787
-9.500 -0.5003 0.07383 0.07025 -0.0540 1.0000 0.0808
-9.250 -0.5487 0.06982 0.06621 -0.0542 1.0000 0.0815
-9.000 -0.6059 0.06820 0.06424 -0.0514 1.0000 0.0825
-8.750 -0.6266 0.06326 0.05915 -0.0498 1.0000 0.0834
-8.500 -0.5546 0.05270 0.04935 -0.0463 0.9971 0.0854
-8.250 -0.5332 0.04882 0.04544 -0.0490 0.9938 0.0874
-8.000 -0.5190 0.04418 0.04063 -0.0529 0.9884 0.0908
-7.750 -0.5079 0.03720 0.03314 -0.0592 0.9831 0.0987
-7.500 -0.5421 0.03334 0.02683 -0.0585 0.9896 0.0501
-7.250 -0.5067 0.03061 0.02392 -0.0609 0.9864 0.0486
-7.000 -0.4694 0.02789 0.02090 -0.0638 0.9838 0.0481
-6.750 -0.4325 0.02608 0.01879 -0.0661 0.9802 0.0485
-6.500 -0.3967 0.02446 0.01694 -0.0680 0.9759 0.0487
-6.250 -0.3585 0.02291 0.01519 -0.0702 0.9727 0.0489
-6.000 -0.3184 0.02165 0.01379 -0.0727 0.9703 0.0493
-5.750 -0.2853 0.02031 0.01239 -0.0739 0.9654 0.0501
-5.500 -0.2497 0.01906 0.01122 -0.0757 0.9611 0.0518
-5.250 -0.2097 0.01818 0.01038 -0.0784 0.9581 0.0544
-5.000 -0.1670 0.01749 0.00966 -0.0815 0.9559 0.0586
-4.750 -0.1325 0.01652 0.00878 -0.0834 0.9498 0.0636
-4.500 -0.0915 0.01571 0.00799 -0.0864 0.9458 0.0723
-4.250 -0.0464 0.01416 0.00695 -0.0910 0.9431 0.1518
-4.000 0.0015 0.01194 0.00650 -0.0972 0.9415 0.5340
-3.750 0.0320 0.01196 0.00678 -0.0971 0.9339 0.6270
-3.500 0.0654 0.01210 0.00693 -0.0974 0.9279 0.6697
-3.250 0.0977 0.01225 0.00703 -0.0976 0.9215 0.6969
-3.000 0.1232 0.01251 0.00730 -0.0961 0.9128 0.7169
-2.750 0.1479 0.01284 0.00763 -0.0941 0.9055 0.7357
-2.500 0.1697 0.01316 0.00795 -0.0916 0.8962 0.7519
-2.250 0.1934 0.01342 0.00818 -0.0897 0.8882 0.7661
-2.000 0.2159 0.01364 0.00837 -0.0876 0.8794 0.7782
-1.750 0.2382 0.01377 0.00847 -0.0856 0.8712 0.7860
-1.500 0.2663 0.01380 0.00844 -0.0853 0.8629 0.7957
-1.250 0.2871 0.01390 0.00852 -0.0830 0.8545 0.8027
-1.000 0.3152 0.01392 0.00847 -0.0827 0.8460 0.8121
-0.750 0.3393 0.01389 0.00842 -0.0815 0.8372 0.8167
-0.500 0.3656 0.01383 0.00831 -0.0808 0.8285 0.8218
-0.250 0.3963 0.01379 0.00822 -0.0814 0.8180 0.8286
0.000 0.4194 0.01368 0.00806 -0.0797 0.8082 0.8335
0.250 0.4444 0.01361 0.00795 -0.0786 0.7960 0.8396
0.500 0.4738 0.01355 0.00785 -0.0789 0.7838 0.8458
0.750 0.4977 0.01345 0.00772 -0.0776 0.7731 0.8502
1.000 0.5250 0.01338 0.00761 -0.0772 0.7622 0.8553
1.250 0.5557 0.01336 0.00756 -0.0778 0.7494 0.8607
1.500 0.5789 0.01323 0.00741 -0.0764 0.7354 0.8649
1.750 0.6050 0.01314 0.00728 -0.0757 0.7199 0.8698
2.000 0.6352 0.01311 0.00720 -0.0762 0.7044 0.8749
2.250 0.6607 0.01302 0.00709 -0.0755 0.6898 0.8786
2.500 0.6867 0.01298 0.00702 -0.0749 0.6742 0.8827
2.750 0.7146 0.01297 0.00699 -0.0748 0.6570 0.8876
3.000 0.7425 0.01298 0.00697 -0.0748 0.6384 0.8919
3.250 0.7667 0.01295 0.00691 -0.0739 0.6188 0.8962
3.500 0.7928 0.01300 0.00689 -0.0734 0.5976 0.9011
3.750 0.8204 0.01310 0.00695 -0.0735 0.5720 0.9060
4.000 0.8423 0.01314 0.00693 -0.0721 0.5459 0.9109
4.250 0.8665 0.01331 0.00699 -0.0714 0.5152 0.9163
4.500 0.8909 0.01356 0.00711 -0.0709 0.4810 0.9212
4.750 0.9110 0.01380 0.00722 -0.0694 0.4452 0.9268
5.000 0.9334 0.01422 0.00747 -0.0687 0.4055 0.9330
5.250 0.9512 0.01458 0.00767 -0.0669 0.3659 0.9395
5.500 0.9711 0.01514 0.00800 -0.0659 0.3237 0.9462
5.750 0.9879 0.01564 0.00833 -0.0641 0.2883 0.9543
6.000 1.0055 0.01622 0.00873 -0.0626 0.2593 0.9638
6.250 1.0254 0.01674 0.00916 -0.0616 0.2353 0.9751
6.500 1.0486 0.01736 0.00967 -0.0613 0.2159 0.9999
6.750 1.0749 0.01816 0.01040 -0.0619 0.2002 1.0000
7.000 1.1015 0.01894 0.01113 -0.0625 0.1875 1.0000
7.250 1.1274 0.01977 0.01191 -0.0629 0.1770 1.0000
7.500 1.1533 0.02057 0.01266 -0.0633 0.1679 1.0000
7.750 1.1795 0.02137 0.01350 -0.0637 0.1603 1.0000
8.000 1.2049 0.02221 0.01430 -0.0640 0.1538 1.0000
8.250 1.2303 0.02316 0.01527 -0.0643 0.1480 1.0000
8.500 1.2550 0.02387 0.01604 -0.0644 0.1417 1.0000
8.750 1.2786 0.02493 0.01700 -0.0645 0.1355 1.0000
9.000 1.3008 0.02551 0.01774 -0.0642 0.1297 1.0000
9.250 1.3223 0.02632 0.01855 -0.0639 0.1247 1.0000
9.500 1.3446 0.02740 0.01965 -0.0637 0.1203 1.0000
9.750 1.3635 0.02812 0.02051 -0.0628 0.1160 1.0000
10.000 1.3805 0.02891 0.02134 -0.0617 0.1120 1.0000
10.250 1.4006 0.03015 0.02253 -0.0613 0.1077 1.0000
10.500 1.4138 0.03091 0.02352 -0.0596 0.1041 1.0000
10.750 1.4274 0.03178 0.02448 -0.0582 0.1000 1.0000
11.000 1.4417 0.03292 0.02557 -0.0571 0.0961 1.0000
11.250 1.4530 0.03410 0.02695 -0.0556 0.0922 1.0000
11.500 1.4622 0.03520 0.02818 -0.0540 0.0878 1.0000
11.750 1.4717 0.03657 0.02950 -0.0527 0.0836 1.0000
12.000 1.4779 0.03811 0.03126 -0.0511 0.0792 1.0000
12.250 1.4841 0.03961 0.03284 -0.0498 0.0750 1.0000
12.500 1.4901 0.04156 0.03476 -0.0485 0.0711 1.0000
12.750 1.4940 0.04353 0.03697 -0.0473 0.0675 1.0000
13.000 1.4986 0.04549 0.03901 -0.0463 0.0644 1.0000
13.250 1.5037 0.04767 0.04112 -0.0452 0.0617 1.0000
13.500 1.5055 0.05019 0.04387 -0.0442 0.0596 1.0000
13.750 1.5070 0.05272 0.04659 -0.0434 0.0575 1.0000
14.000 1.5088 0.05522 0.04921 -0.0428 0.0557 1.0000
14.250 1.5107 0.05772 0.05176 -0.0424 0.0541 1.0000
14.500 1.5142 0.06029 0.05431 -0.0416 0.0524 1.0000
14.750 1.5109 0.06364 0.05788 -0.0413 0.0513 1.0000
15.000 1.5051 0.06730 0.06178 -0.0413 0.0504 1.0000
15.250 1.4986 0.07120 0.06590 -0.0415 0.0495 1.0000
15.500 1.4915 0.07528 0.07018 -0.0421 0.0486 1.0000
15.750 1.4840 0.07955 0.07463 -0.0429 0.0478 1.0000
16.000 1.4763 0.08398 0.07922 -0.0440 0.0471 1.0000
16.250 1.4695 0.08838 0.08375 -0.0453 0.0464 1.0000
16.500 1.4645 0.09257 0.08803 -0.0466 0.0457 1.0000
16.750 1.4615 0.09643 0.09194 -0.0477 0.0448 1.0000
17.000 1.4503 0.10174 0.09736 -0.0493 0.0441 1.0000
17.250 1.4295 0.10914 0.10501 -0.0532 0.0439 1.0000
17.500 1.4055 0.11758 0.11370 -0.0581 0.0437 1.0000
17.750 1.3777 0.12722 0.12361 -0.0642 0.0437 1.0000
18.000 1.3433 0.13894 0.13558 -0.0721 0.0438 1.0000
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Polar data table (+)
Polar graphs
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