NASA/LANGLEY LS(1)-0413MOD AIRFOIL (ls413mod-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY LS(1)-0413MOD AIRFOIL (ls413mod-il) Reynolds number: 200,000 Max Cl/Cd: 62.04 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ls413mod-il-200000-n5.txt Download as CSV file: xf-ls413mod-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.6381 0.06309 0.05869 -0.0624 1.0000 0.0243
-11.500 -0.6588 0.05760 0.05305 -0.0657 1.0000 0.0242
-11.250 -0.6785 0.05339 0.04869 -0.0667 1.0000 0.0242
-11.000 -0.6993 0.05029 0.04546 -0.0654 1.0000 0.0241
-10.750 -0.7137 0.04716 0.04214 -0.0643 1.0000 0.0241
-10.500 -0.7227 0.04425 0.03900 -0.0625 1.0000 0.0241
-10.250 -0.7273 0.04153 0.03601 -0.0606 1.0000 0.0241
-10.000 -0.7276 0.03904 0.03326 -0.0586 1.0000 0.0242
-9.750 -0.7165 0.03637 0.03024 -0.0586 0.9984 0.0242
-9.500 -0.6901 0.03352 0.02700 -0.0610 0.9945 0.0244
-9.250 -0.6626 0.03113 0.02436 -0.0630 0.9906 0.0246
-9.000 -0.6329 0.02919 0.02222 -0.0649 0.9866 0.0249
-8.750 -0.6008 0.02751 0.02036 -0.0670 0.9833 0.0251
-8.500 -0.5701 0.02612 0.01883 -0.0686 0.9788 0.0256
-8.250 -0.5381 0.02490 0.01747 -0.0703 0.9745 0.0262
-8.000 -0.5045 0.02373 0.01616 -0.0722 0.9713 0.0269
-7.750 -0.4726 0.02260 0.01488 -0.0736 0.9672 0.0275
-7.500 -0.4420 0.02153 0.01369 -0.0745 0.9617 0.0280
-7.250 -0.4090 0.02051 0.01256 -0.0759 0.9576 0.0285
-7.000 -0.3769 0.01962 0.01158 -0.0771 0.9529 0.0290
-6.750 -0.3469 0.01873 0.01066 -0.0780 0.9465 0.0295
-6.500 -0.3142 0.01785 0.00979 -0.0795 0.9418 0.0304
-6.250 -0.2834 0.01718 0.00912 -0.0805 0.9352 0.0313
-6.000 -0.2519 0.01655 0.00847 -0.0816 0.9286 0.0324
-5.750 -0.2190 0.01600 0.00786 -0.0829 0.9232 0.0342
-5.500 -0.1891 0.01545 0.00731 -0.0836 0.9151 0.0363
-5.250 -0.1566 0.01497 0.00681 -0.0848 0.9092 0.0388
-4.750 -0.0952 0.01412 0.00591 -0.0863 0.8941 0.0467
-4.500 -0.0649 0.01371 0.00552 -0.0870 0.8862 0.0572
-4.250 -0.0339 0.01321 0.00513 -0.0879 0.8786 0.0831
-4.000 -0.0028 0.01261 0.00480 -0.0891 0.8708 0.1427
-3.750 0.0294 0.01185 0.00447 -0.0908 0.8629 0.2517
-3.500 0.0632 0.01094 0.00422 -0.0930 0.8553 0.4111
-3.250 0.0941 0.01049 0.00425 -0.0938 0.8468 0.5354
-3.000 0.1221 0.01047 0.00443 -0.0934 0.8383 0.6102
-2.750 0.1503 0.01056 0.00455 -0.0930 0.8292 0.6521
-2.500 0.1788 0.01068 0.00463 -0.0928 0.8200 0.6801
-2.250 0.2062 0.01081 0.00472 -0.0922 0.8113 0.6986
-2.000 0.2345 0.01091 0.00479 -0.0920 0.8021 0.7125
-1.750 0.2616 0.01100 0.00483 -0.0914 0.7941 0.7206
-1.500 0.2907 0.01107 0.00485 -0.0915 0.7851 0.7310
-1.250 0.3176 0.01116 0.00491 -0.0909 0.7773 0.7377
-1.000 0.3470 0.01120 0.00489 -0.0912 0.7680 0.7433
-0.750 0.3766 0.01123 0.00484 -0.0914 0.7597 0.7482
-0.500 0.4039 0.01129 0.00490 -0.0910 0.7495 0.7528
-0.250 0.4323 0.01135 0.00491 -0.0909 0.7382 0.7586
0.000 0.4615 0.01140 0.00488 -0.0911 0.7251 0.7644
0.250 0.4884 0.01146 0.00489 -0.0906 0.7107 0.7681
0.500 0.5162 0.01153 0.00491 -0.0904 0.6966 0.7723
0.750 0.5453 0.01159 0.00493 -0.0905 0.6830 0.7773
1.000 0.5741 0.01166 0.00497 -0.0907 0.6699 0.7816
1.250 0.6010 0.01175 0.00501 -0.0903 0.6527 0.7848
1.500 0.6283 0.01185 0.00503 -0.0900 0.6314 0.7882
1.750 0.6563 0.01197 0.00507 -0.0900 0.6089 0.7921
2.000 0.6853 0.01210 0.00512 -0.0902 0.5880 0.7965
2.250 0.7115 0.01225 0.00522 -0.0898 0.5660 0.7993
2.500 0.7378 0.01243 0.00532 -0.0894 0.5417 0.8026
2.750 0.7642 0.01265 0.00545 -0.0891 0.5155 0.8065
3.000 0.7912 0.01292 0.00560 -0.0890 0.4867 0.8108
3.250 0.8167 0.01322 0.00578 -0.0886 0.4560 0.8145
3.500 0.8409 0.01356 0.00600 -0.0879 0.4246 0.8177
3.750 0.8654 0.01395 0.00626 -0.0874 0.3920 0.8213
4.000 0.8900 0.01439 0.00654 -0.0870 0.3566 0.8255
4.250 0.9144 0.01488 0.00686 -0.0866 0.3210 0.8297
4.500 0.9367 0.01536 0.00721 -0.0858 0.2894 0.8330
4.750 0.9598 0.01586 0.00759 -0.0851 0.2619 0.8368
5.000 0.9838 0.01634 0.00799 -0.0847 0.2388 0.8410
5.250 1.0081 0.01684 0.00840 -0.0843 0.2177 0.8455
5.500 1.0301 0.01730 0.00882 -0.0834 0.2005 0.8492
5.750 1.0530 0.01776 0.00925 -0.0827 0.1860 0.8536
6.000 1.0768 0.01824 0.00971 -0.0823 0.1736 0.8582
6.250 1.0993 0.01873 0.01019 -0.0815 0.1633 0.8623
6.500 1.1208 0.01919 0.01066 -0.0806 0.1543 0.8668
6.750 1.1429 0.01969 0.01118 -0.0798 0.1471 0.8721
7.000 1.1646 0.02021 0.01172 -0.0790 0.1402 0.8771
7.250 1.1843 0.02074 0.01228 -0.0777 0.1345 0.8818
7.500 1.2055 0.02124 0.01285 -0.0768 0.1289 0.8873
7.750 1.2247 0.02184 0.01346 -0.0756 0.1242 0.8929
8.000 1.2426 0.02242 0.01409 -0.0741 0.1204 0.8991
8.250 1.2629 0.02295 0.01473 -0.0731 0.1161 0.9057
8.500 1.2793 0.02351 0.01533 -0.0714 0.1115 0.9123
9.000 1.3119 0.02463 0.01660 -0.0681 0.1025 0.9284
9.250 1.3242 0.02517 0.01720 -0.0658 0.0983 0.9398
9.750 1.3501 0.02645 0.01863 -0.0618 0.0916 1.0000
10.000 1.3681 0.02726 0.01952 -0.0611 0.0880 1.0000
10.250 1.3839 0.02820 0.02051 -0.0601 0.0847 1.0000
10.500 1.3989 0.02922 0.02158 -0.0591 0.0817 1.0000
10.750 1.4153 0.03013 0.02262 -0.0582 0.0783 1.0000
11.000 1.4296 0.03119 0.02375 -0.0573 0.0750 1.0000
11.250 1.4410 0.03247 0.02507 -0.0562 0.0721 1.0000
11.500 1.4546 0.03363 0.02636 -0.0552 0.0692 1.0000
11.750 1.4671 0.03488 0.02773 -0.0543 0.0657 1.0000
12.000 1.4765 0.03638 0.02928 -0.0533 0.0625 1.0000
12.250 1.4863 0.03792 0.03092 -0.0524 0.0593 1.0000
12.500 1.4958 0.03951 0.03263 -0.0515 0.0558 1.0000
12.750 1.5016 0.04146 0.03464 -0.0507 0.0528 1.0000
13.000 1.5083 0.04340 0.03671 -0.0499 0.0498 1.0000
13.250 1.5137 0.04551 0.03894 -0.0493 0.0470 1.0000
13.500 1.5160 0.04797 0.04147 -0.0487 0.0448 1.0000
13.750 1.5177 0.05058 0.04419 -0.0483 0.0429 1.0000
14.000 1.5190 0.05330 0.04705 -0.0479 0.0411 1.0000
14.250 1.5184 0.05630 0.05017 -0.0478 0.0395 1.0000
14.500 1.5156 0.05964 0.05362 -0.0479 0.0383 1.0000
14.750 1.5101 0.06345 0.05753 -0.0483 0.0373 1.0000
15.000 1.5059 0.06722 0.06145 -0.0488 0.0363 1.0000
15.250 1.5006 0.07128 0.06566 -0.0496 0.0354 1.0000
15.500 1.4941 0.07565 0.07018 -0.0506 0.0346 1.0000
15.750 1.4862 0.08039 0.07506 -0.0520 0.0339 1.0000
16.000 1.4767 0.08548 0.08030 -0.0537 0.0333 1.0000
16.250 1.4657 0.09098 0.08593 -0.0558 0.0327 1.0000
16.500 1.4537 0.09681 0.09188 -0.0582 0.0323 1.0000
16.750 1.4407 0.10292 0.09812 -0.0608 0.0319 1.0000
17.000 1.4272 0.10918 0.10448 -0.0637 0.0315 1.0000
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Polar data table (+)
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