NASA/LANGLEY LS(1)-0413MOD AIRFOIL (ls413mod-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY LS(1)-0413MOD AIRFOIL (ls413mod-il) Reynolds number: 100,000 Max Cl/Cd: 53.31 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ls413mod-il-100000.txt Download as CSV file: xf-ls413mod-il-100000.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 = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4570 0.09290 0.08792 -0.0397 1.0000 0.1580
-9.250 -0.4197 0.09132 0.08628 -0.0347 1.0000 0.1629
-9.000 -0.4496 0.08767 0.08278 -0.0383 1.0000 0.1713
-8.750 -0.4581 0.08379 0.07900 -0.0378 1.0000 0.1752
-8.500 -0.4358 0.08200 0.07720 -0.0349 1.0000 0.1805
-8.250 -0.4837 0.07876 0.07418 -0.0355 1.0000 0.1866
-8.000 -0.5220 0.07447 0.06998 -0.0365 1.0000 0.1910
-7.750 -0.5010 0.07335 0.06893 -0.0317 1.0000 0.1956
-7.000 -0.5572 0.04386 0.03722 -0.0471 1.0000 0.0938
-6.750 -0.5349 0.03911 0.03150 -0.0479 1.0000 0.0823
-6.500 -0.5146 0.03601 0.02825 -0.0481 1.0000 0.0805
-6.250 -0.4917 0.03353 0.02547 -0.0483 1.0000 0.0790
-6.000 -0.4671 0.03142 0.02304 -0.0485 1.0000 0.0779
-5.750 -0.4413 0.02968 0.02098 -0.0487 1.0000 0.0775
-5.500 -0.4159 0.02837 0.01943 -0.0488 1.0000 0.0786
-5.250 -0.3910 0.02738 0.01823 -0.0488 1.0000 0.0808
-5.000 -0.3662 0.02658 0.01721 -0.0486 1.0000 0.0826
-4.750 -0.3414 0.02526 0.01593 -0.0485 1.0000 0.0846
-4.500 -0.3059 0.02429 0.01505 -0.0503 0.9971 0.0887
-4.250 -0.2627 0.02359 0.01429 -0.0534 0.9928 0.0959
-4.000 -0.2215 0.02266 0.01354 -0.0566 0.9876 0.1100
-3.750 -0.1726 0.02111 0.01253 -0.0616 0.9844 0.1647
-3.500 -0.1316 0.01955 0.01350 -0.0638 0.9821 0.6658
-3.250 -0.1072 0.02054 0.01447 -0.0615 0.9727 0.7174
-3.000 -0.0881 0.02154 0.01546 -0.0578 0.9634 0.7519
-2.750 -0.0656 0.02247 0.01633 -0.0545 0.9557 0.7831
-2.500 -0.0548 0.02307 0.01690 -0.0493 0.9449 0.8084
-2.250 -0.0381 0.02347 0.01725 -0.0453 0.9363 0.8333
-2.000 -0.0201 0.02362 0.01733 -0.0419 0.9273 0.8567
-1.750 -0.0018 0.02361 0.01725 -0.0393 0.9180 0.8771
-1.500 0.0246 0.02339 0.01694 -0.0380 0.9104 0.8948
-1.250 0.0453 0.02321 0.01668 -0.0364 0.9007 0.9105
-1.000 0.0805 0.02288 0.01626 -0.0373 0.8941 0.9253
-0.750 0.1072 0.02272 0.01603 -0.0374 0.8845 0.9366
-0.500 0.1512 0.02244 0.01567 -0.0405 0.8782 0.9451
-0.250 0.1873 0.02227 0.01544 -0.0423 0.8696 0.9544
0.000 0.2356 0.02197 0.01508 -0.0462 0.8629 0.9625
0.250 0.2950 0.02155 0.01460 -0.0518 0.8588 0.9679
0.500 0.3335 0.02142 0.01446 -0.0543 0.8473 0.9748
0.750 0.3896 0.02095 0.01396 -0.0592 0.8403 0.9789
1.000 0.4375 0.02051 0.01351 -0.0627 0.8296 0.9838
1.250 0.4880 0.02008 0.01308 -0.0667 0.8182 0.9877
1.500 0.5405 0.01931 0.01229 -0.0704 0.8099 0.9914
1.750 0.5803 0.01899 0.01200 -0.0726 0.7957 0.9965
2.000 0.6116 0.01876 0.01179 -0.0731 0.7818 1.0000
2.250 0.6318 0.01854 0.01157 -0.0715 0.7676 1.0000
2.500 0.6530 0.01823 0.01124 -0.0698 0.7525 1.0000
2.750 0.6741 0.01791 0.01092 -0.0680 0.7366 1.0000
3.000 0.6947 0.01764 0.01062 -0.0663 0.7201 1.0000
3.250 0.7157 0.01743 0.01041 -0.0647 0.7035 1.0000
3.500 0.7390 0.01725 0.01023 -0.0636 0.6860 1.0000
3.750 0.7649 0.01709 0.01004 -0.0630 0.6671 1.0000
4.000 0.7932 0.01693 0.00984 -0.0628 0.6471 1.0000
4.250 0.8195 0.01691 0.00983 -0.0624 0.6227 1.0000
4.500 0.8487 0.01684 0.00969 -0.0624 0.5976 1.0000
4.750 0.8756 0.01692 0.00972 -0.0623 0.5665 1.0000
5.000 0.9026 0.01708 0.00979 -0.0621 0.5314 1.0000
5.250 0.9281 0.01741 0.00998 -0.0618 0.4898 1.0000
5.500 0.9524 0.01794 0.01028 -0.0614 0.4440 1.0000
5.750 0.9752 0.01870 0.01075 -0.0609 0.3968 1.0000
6.000 0.9973 0.01965 0.01139 -0.0605 0.3532 1.0000
6.250 1.0199 0.02067 0.01216 -0.0602 0.3160 1.0000
6.500 1.0435 0.02179 0.01302 -0.0602 0.2879 1.0000
6.750 1.0684 0.02287 0.01398 -0.0603 0.2651 1.0000
7.000 1.0941 0.02397 0.01494 -0.0605 0.2473 1.0000
7.250 1.1206 0.02508 0.01598 -0.0609 0.2327 1.0000
7.500 1.1481 0.02625 0.01713 -0.0614 0.2209 1.0000
7.750 1.1771 0.02753 0.01825 -0.0621 0.2109 1.0000
8.000 1.2028 0.02860 0.01947 -0.0622 0.2013 1.0000
8.250 1.2309 0.02995 0.02078 -0.0628 0.1933 1.0000
8.500 1.2570 0.03117 0.02215 -0.0630 0.1860 1.0000
8.750 1.2869 0.03278 0.02366 -0.0639 0.1798 1.0000
9.000 1.3081 0.03401 0.02520 -0.0633 0.1731 1.0000
9.250 1.3364 0.03545 0.02643 -0.0641 0.1657 1.0000
9.500 1.3515 0.03654 0.02793 -0.0627 0.1589 1.0000
9.750 1.3766 0.03774 0.02900 -0.0629 0.1519 1.0000
10.000 1.3915 0.03931 0.03090 -0.0616 0.1460 1.0000
10.250 1.4099 0.04050 0.03220 -0.0608 0.1397 1.0000
10.500 1.4278 0.04231 0.03411 -0.0602 0.1338 1.0000
10.750 1.4383 0.04381 0.03590 -0.0583 0.1278 1.0000
11.000 1.4615 0.04559 0.03752 -0.0585 0.1215 1.0000
11.250 1.4600 0.04749 0.03992 -0.0552 0.1165 1.0000
11.500 1.4718 0.04892 0.04142 -0.0537 0.1110 1.0000
11.750 1.4787 0.05139 0.04403 -0.0520 0.1062 1.0000
12.000 1.4686 0.05371 0.04673 -0.0481 0.1026 1.0000
12.250 1.4704 0.05548 0.04861 -0.0457 0.0987 1.0000
12.500 1.4866 0.05809 0.05113 -0.0454 0.0946 1.0000
12.750 1.4628 0.06133 0.05480 -0.0413 0.0934 1.0000
13.000 1.4383 0.06524 0.05910 -0.0383 0.0922 1.0000
13.250 1.4126 0.06978 0.06398 -0.0365 0.0912 1.0000
13.500 1.3837 0.07511 0.06964 -0.0357 0.0905 1.0000
13.750 1.3486 0.08171 0.07655 -0.0363 0.0903 1.0000
14.000 1.3037 0.09040 0.08556 -0.0389 0.0909 1.0000
14.250 1.2481 0.10206 0.09749 -0.0445 0.0923 1.0000
14.500 1.1849 0.11751 0.11312 -0.0537 0.0940 1.0000
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Polar data table (+)
Polar graphs
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