NASA/LANGLEY LS(1)-0417 (GA(W)-1) AIRFOIL (ls417-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY LS(1)-0417 (GA(W)-1) AIRFOIL (ls417-il) Reynolds number: 100,000 Max Cl/Cd: 41.01 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ls417-il-100000-n5.txt Download as CSV file: xf-ls417-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY LS(1)-0417 (GA(W)-1) 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.5760 0.08280 0.07667 -0.0793 1.0000 0.0348
-13.250 -0.6422 0.07102 0.06452 -0.0857 1.0000 0.0342
-13.000 -0.6812 0.06569 0.05899 -0.0860 1.0000 0.0340
-12.750 -0.7160 0.06250 0.05566 -0.0834 1.0000 0.0339
-12.500 -0.7435 0.05981 0.05282 -0.0810 0.9983 0.0339
-12.250 -0.7444 0.05603 0.04877 -0.0835 0.9918 0.0341
-12.000 -0.7420 0.05279 0.04529 -0.0853 0.9845 0.0343
-11.750 -0.7358 0.04990 0.04215 -0.0869 0.9781 0.0347
-11.500 -0.7278 0.04739 0.03940 -0.0879 0.9711 0.0351
-11.250 -0.7153 0.04500 0.03675 -0.0892 0.9656 0.0359
-11.000 -0.7043 0.04280 0.03424 -0.0895 0.9583 0.0367
-10.750 -0.6860 0.04061 0.03171 -0.0906 0.9540 0.0377
-10.500 -0.6637 0.03927 0.03033 -0.0914 0.9497 0.0385
-10.250 -0.6455 0.03798 0.02894 -0.0912 0.9436 0.0393
-10.000 -0.6214 0.03651 0.02731 -0.0918 0.9395 0.0402
-9.750 -0.5945 0.03504 0.02565 -0.0926 0.9364 0.0413
-9.500 -0.5729 0.03386 0.02432 -0.0923 0.9317 0.0424
-9.250 -0.5535 0.03295 0.02343 -0.0918 0.9264 0.0433
-9.000 -0.5299 0.03200 0.02243 -0.0919 0.9225 0.0449
-8.750 -0.5038 0.03104 0.02132 -0.0924 0.9194 0.0472
-8.500 -0.4786 0.03011 0.02042 -0.0930 0.9164 0.0494
-8.250 -0.4645 0.02951 0.01977 -0.0913 0.9095 0.0516
-8.000 -0.4435 0.02870 0.01893 -0.0909 0.9050 0.0541
-7.750 -0.4206 0.02786 0.01809 -0.0910 0.9016 0.0571
-7.500 -0.3962 0.02703 0.01723 -0.0913 0.8989 0.0613
-7.250 -0.3784 0.02645 0.01664 -0.0905 0.8943 0.0667
-7.000 -0.3619 0.02589 0.01611 -0.0894 0.8891 0.0731
-6.750 -0.3398 0.02523 0.01551 -0.0893 0.8851 0.0828
-6.500 -0.3146 0.02453 0.01490 -0.0897 0.8820 0.0979
-6.250 -0.2876 0.02381 0.01430 -0.0904 0.8795 0.1210
-6.000 -0.2645 0.02319 0.01385 -0.0905 0.8762 0.1516
-5.750 -0.2484 0.02271 0.01364 -0.0895 0.8708 0.1942
-5.500 -0.2265 0.02188 0.01329 -0.0899 0.8671 0.2743
-5.250 -0.2007 0.02104 0.01297 -0.0909 0.8642 0.3726
-5.000 -0.1739 0.02065 0.01302 -0.0909 0.8617 0.4570
-4.750 -0.1485 0.02092 0.01360 -0.0894 0.8594 0.5185
-4.500 -0.1221 0.02136 0.01410 -0.0883 0.8570 0.5657
-4.250 -0.1055 0.02199 0.01472 -0.0863 0.8512 0.5973
-4.000 -0.0793 0.02237 0.01500 -0.0862 0.8475 0.6255
-3.750 -0.0517 0.02275 0.01528 -0.0860 0.8444 0.6440
-3.500 -0.0257 0.02322 0.01570 -0.0848 0.8417 0.6565
-3.250 0.0019 0.02363 0.01603 -0.0840 0.8396 0.6693
-3.000 0.0317 0.02396 0.01628 -0.0839 0.8379 0.6841
-2.750 0.0394 0.02479 0.01712 -0.0798 0.8309 0.6920
-2.500 0.0643 0.02503 0.01728 -0.0797 0.8268 0.7031
-2.250 0.0875 0.02531 0.01753 -0.0783 0.8236 0.7080
-2.000 0.1168 0.02538 0.01753 -0.0785 0.8211 0.7147
-1.750 0.1500 0.02533 0.01739 -0.0798 0.8192 0.7220
-1.500 0.1780 0.02545 0.01747 -0.0793 0.8174 0.7266
-1.250 0.1849 0.02613 0.01817 -0.0764 0.8089 0.7333
-1.000 0.2124 0.02624 0.01824 -0.0768 0.8051 0.7403
-0.750 0.2377 0.02636 0.01835 -0.0759 0.8021 0.7447
-0.500 0.2689 0.02633 0.01828 -0.0764 0.7998 0.7501
-0.250 0.3070 0.02616 0.01805 -0.0788 0.7980 0.7563
0.000 0.3113 0.02685 0.01879 -0.0750 0.7886 0.7597
0.250 0.3376 0.02687 0.01881 -0.0747 0.7842 0.7633
0.500 0.3710 0.02669 0.01862 -0.0756 0.7812 0.7673
0.750 0.4094 0.02640 0.01830 -0.0776 0.7790 0.7715
1.250 0.4490 0.02687 0.01883 -0.0755 0.7647 0.7778
1.500 0.4833 0.02655 0.01852 -0.0764 0.7613 0.7806
1.750 0.5239 0.02596 0.01792 -0.0781 0.7585 0.7833
2.000 0.5376 0.02634 0.01835 -0.0763 0.7462 0.7871
2.250 0.5816 0.02553 0.01753 -0.0787 0.7412 0.7902
2.500 0.6033 0.02547 0.01752 -0.0776 0.7313 0.7924
2.750 0.6355 0.02488 0.01696 -0.0777 0.7234 0.7946
3.000 0.6610 0.02457 0.01669 -0.0769 0.7132 0.7973
3.500 0.7157 0.02389 0.01611 -0.0763 0.6903 0.8027
3.750 0.7551 0.02319 0.01541 -0.0778 0.6817 0.8051
4.000 0.7744 0.02332 0.01562 -0.0767 0.6659 0.8082
4.250 0.7904 0.02332 0.01570 -0.0745 0.6491 0.8107
4.500 0.8099 0.02318 0.01560 -0.0727 0.6298 0.8134
4.750 0.8270 0.02315 0.01560 -0.0708 0.6056 0.8162
5.000 0.8554 0.02276 0.01515 -0.0704 0.5729 0.8188
5.250 0.8904 0.02229 0.01443 -0.0709 0.5254 0.8212
5.500 0.9173 0.02237 0.01414 -0.0705 0.4692 0.8239
5.750 0.9303 0.02296 0.01442 -0.0681 0.4210 0.8264
6.000 0.9395 0.02374 0.01496 -0.0653 0.3787 0.8292
6.250 0.9502 0.02464 0.01565 -0.0630 0.3405 0.8325
6.500 0.9623 0.02562 0.01643 -0.0612 0.3075 0.8361
6.750 0.9769 0.02659 0.01725 -0.0600 0.2782 0.8396
7.000 0.9914 0.02759 0.01810 -0.0588 0.2540 0.8426
7.250 1.0043 0.02849 0.01891 -0.0572 0.2345 0.8453
7.750 1.0337 0.03034 0.02064 -0.0548 0.2028 0.8517
8.000 1.0505 0.03126 0.02154 -0.0540 0.1902 0.8552
8.250 1.0667 0.03226 0.02250 -0.0532 0.1797 0.8590
8.500 1.0798 0.03318 0.02341 -0.0517 0.1708 0.8625
8.750 1.0948 0.03411 0.02436 -0.0506 0.1632 0.8666
9.000 1.1099 0.03514 0.02538 -0.0496 0.1563 0.8708
9.250 1.1263 0.03620 0.02643 -0.0489 0.1502 0.8748
9.500 1.1407 0.03712 0.02742 -0.0477 0.1445 0.8785
9.750 1.1540 0.03822 0.02848 -0.0466 0.1399 0.8827
10.000 1.1710 0.03921 0.02955 -0.0458 0.1351 0.8872
10.250 1.1867 0.04023 0.03064 -0.0450 0.1307 0.8917
10.500 1.1997 0.04130 0.03170 -0.0438 0.1271 0.8968
10.750 1.2154 0.04234 0.03282 -0.0429 0.1234 0.9027
11.000 1.2293 0.04337 0.03396 -0.0418 0.1197 0.9087
11.250 1.2423 0.04446 0.03509 -0.0406 0.1165 0.9156
11.500 1.2551 0.04557 0.03618 -0.0395 0.1138 0.9228
11.750 1.2675 0.04670 0.03751 -0.0383 0.1104 0.9313
12.000 1.2782 0.04785 0.03877 -0.0370 0.1074 0.9422
12.500 1.2986 0.05027 0.04126 -0.0351 0.1024 1.0000
12.750 1.3124 0.05196 0.04315 -0.0350 0.0994 1.0000
13.000 1.3251 0.05367 0.04497 -0.0349 0.0966 1.0000
13.250 1.3375 0.05536 0.04667 -0.0348 0.0944 1.0000
13.500 1.3497 0.05715 0.04851 -0.0347 0.0922 1.0000
13.750 1.3579 0.05929 0.05087 -0.0344 0.0897 1.0000
14.000 1.3658 0.06139 0.05311 -0.0342 0.0874 1.0000
14.250 1.3744 0.06340 0.05517 -0.0340 0.0855 1.0000
14.500 1.3851 0.06524 0.05695 -0.0339 0.0838 1.0000
14.750 1.3857 0.06821 0.06023 -0.0337 0.0818 1.0000
15.000 1.3872 0.07107 0.06330 -0.0336 0.0798 1.0000
15.250 1.3897 0.07382 0.06618 -0.0336 0.0781 1.0000
15.500 1.3945 0.07629 0.06870 -0.0337 0.0766 1.0000
15.750 1.4000 0.07873 0.07114 -0.0338 0.0752 1.0000
16.000 1.3907 0.08315 0.07590 -0.0344 0.0737 1.0000
16.250 1.3828 0.08749 0.08049 -0.0352 0.0722 1.0000
16.500 1.3763 0.09173 0.08491 -0.0362 0.0709 1.0000
16.750 1.3722 0.09569 0.08901 -0.0374 0.0697 1.0000
17.000 1.3736 0.09890 0.09227 -0.0384 0.0686 1.0000
17.250 1.3708 0.10283 0.09628 -0.0398 0.0676 1.0000
17.500 1.3437 0.11103 0.10487 -0.0436 0.0666 1.0000
17.750 1.3112 0.12078 0.11499 -0.0490 0.0658 1.0000
18.000 1.2530 0.13684 0.13149 -0.0593 0.0652 1.0000
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Polar data table (+)
Polar graphs
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