NASA/LANGLEY LS(1)-0413 (GA(W)-2) AIRFOIL (ls413-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NASA/LANGLEY LS(1)-0413 (GA(W)-2) AIRFOIL (ls413-il) Reynolds number: 100,000 Max Cl/Cd: 48.85 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ls413-il-100000-n5.txt Download as CSV file: xf-ls413-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.4670 0.09408 0.08855 -0.0534 1.0000 0.0397
-10.750 -0.4786 0.08779 0.08232 -0.0563 1.0000 0.0391
-10.500 -0.5070 0.07802 0.07259 -0.0620 1.0000 0.0381
-10.250 -0.5542 0.07020 0.06474 -0.0649 1.0000 0.0372
-10.000 -0.6012 0.06659 0.06111 -0.0620 1.0000 0.0368
-9.750 -0.6423 0.06369 0.05814 -0.0583 1.0000 0.0364
-9.500 -0.6631 0.05862 0.05275 -0.0590 0.9969 0.0361
-9.250 -0.6534 0.05399 0.04777 -0.0626 0.9912 0.0363
-9.000 -0.6372 0.05047 0.04396 -0.0653 0.9859 0.0368
-8.750 -0.6172 0.04697 0.04011 -0.0682 0.9818 0.0375
-8.500 -0.5990 0.04377 0.03653 -0.0697 0.9764 0.0380
-8.250 -0.5753 0.04057 0.03289 -0.0718 0.9725 0.0383
-8.000 -0.5473 0.03762 0.02949 -0.0741 0.9697 0.0385
-7.750 -0.5239 0.03533 0.02684 -0.0747 0.9646 0.0388
-7.500 -0.4957 0.03323 0.02440 -0.0760 0.9608 0.0393
-7.250 -0.4647 0.03136 0.02220 -0.0774 0.9580 0.0399
-7.000 -0.4319 0.02971 0.02027 -0.0790 0.9559 0.0407
-6.750 -0.4057 0.02850 0.01881 -0.0791 0.9513 0.0416
-6.500 -0.3776 0.02729 0.01758 -0.0798 0.9474 0.0432
-6.250 -0.3466 0.02633 0.01660 -0.0810 0.9445 0.0452
-6.000 -0.3141 0.02537 0.01557 -0.0823 0.9422 0.0472
-5.750 -0.2806 0.02443 0.01454 -0.0837 0.9405 0.0491
-5.500 -0.2583 0.02369 0.01379 -0.0830 0.9348 0.0509
-5.250 -0.2286 0.02292 0.01308 -0.0841 0.9312 0.0542
-5.000 -0.1955 0.02230 0.01239 -0.0856 0.9284 0.0593
-4.750 -0.1610 0.02154 0.01166 -0.0875 0.9263 0.0651
-4.500 -0.1262 0.02091 0.01104 -0.0894 0.9244 0.0750
-4.250 -0.1033 0.02049 0.01067 -0.0891 0.9186 0.0887
-4.000 -0.0718 0.01963 0.01018 -0.0907 0.9154 0.1442
-3.750 -0.0355 0.01790 0.00974 -0.0945 0.9135 0.4026
-3.500 -0.0087 0.01775 0.01036 -0.0936 0.9108 0.5716
-3.250 0.0232 0.01805 0.01068 -0.0937 0.9085 0.6391
-3.000 0.0384 0.01875 0.01142 -0.0904 0.9014 0.6844
-2.750 0.0593 0.01940 0.01208 -0.0875 0.8970 0.7167
-2.500 0.0880 0.01964 0.01224 -0.0870 0.8940 0.7327
-2.250 0.1149 0.01975 0.01226 -0.0867 0.8898 0.7409
-2.000 0.1392 0.01989 0.01232 -0.0862 0.8843 0.7485
-1.750 0.1669 0.02000 0.01237 -0.0860 0.8807 0.7574
-1.500 0.1974 0.02004 0.01235 -0.0863 0.8779 0.7658
-1.250 0.2246 0.02012 0.01238 -0.0862 0.8738 0.7725
-1.000 0.2498 0.02026 0.01248 -0.0860 0.8677 0.7794
-0.750 0.2774 0.02028 0.01247 -0.0857 0.8637 0.7850
-0.500 0.3114 0.02023 0.01238 -0.0870 0.8610 0.7919
-0.250 0.3341 0.02040 0.01255 -0.0862 0.8548 0.7972
0.000 0.3604 0.02046 0.01262 -0.0860 0.8497 0.8020
0.250 0.3938 0.02040 0.01254 -0.0872 0.8463 0.8071
0.500 0.4283 0.02030 0.01244 -0.0885 0.8434 0.8112
0.750 0.4478 0.02046 0.01264 -0.0870 0.8343 0.8151
1.000 0.4825 0.02018 0.01236 -0.0879 0.8295 0.8190
1.250 0.5097 0.02013 0.01235 -0.0879 0.8202 0.8234
1.500 0.5441 0.01982 0.01205 -0.0887 0.8138 0.8271
1.750 0.5691 0.01965 0.01193 -0.0877 0.8031 0.8307
2.000 0.6021 0.01913 0.01143 -0.0878 0.7922 0.8344
2.250 0.6350 0.01863 0.01094 -0.0880 0.7794 0.8385
2.500 0.6621 0.01843 0.01078 -0.0875 0.7652 0.8427
2.750 0.6871 0.01822 0.01065 -0.0865 0.7509 0.8464
3.000 0.7142 0.01798 0.01044 -0.0859 0.7340 0.8505
3.250 0.7429 0.01774 0.01023 -0.0856 0.7149 0.8551
3.500 0.7664 0.01767 0.01024 -0.0845 0.6914 0.8594
3.750 0.7917 0.01750 0.01008 -0.0835 0.6644 0.8634
4.000 0.8171 0.01741 0.00997 -0.0827 0.6264 0.8680
4.250 0.8449 0.01735 0.00968 -0.0820 0.5625 0.8728
4.500 0.8641 0.01769 0.00955 -0.0798 0.4804 0.8774
4.750 0.8789 0.01851 0.00988 -0.0775 0.4009 0.8829
5.000 0.8945 0.01941 0.01042 -0.0757 0.3351 0.8883
5.250 0.9086 0.02021 0.01094 -0.0735 0.2865 0.8938
5.500 0.9256 0.02099 0.01152 -0.0720 0.2486 0.9002
5.750 0.9420 0.02167 0.01206 -0.0703 0.2193 0.9070
6.000 0.9593 0.02233 0.01264 -0.0688 0.1973 0.9149
6.250 0.9759 0.02296 0.01321 -0.0671 0.1808 0.9233
6.500 0.9928 0.02363 0.01383 -0.0656 0.1674 0.9330
6.750 1.0096 0.02427 0.01446 -0.0641 0.1563 0.9452
7.000 1.0272 0.02486 0.01511 -0.0627 0.1468 0.9655
7.250 1.0445 0.02565 0.01585 -0.0616 0.1389 1.0000
7.500 1.0675 0.02645 0.01673 -0.0615 0.1305 1.0000
7.750 1.0876 0.02745 0.01765 -0.0611 0.1240 1.0000
8.000 1.1102 0.02831 0.01863 -0.0608 0.1175 1.0000
8.250 1.1300 0.02930 0.01960 -0.0603 0.1119 1.0000
8.500 1.1511 0.03030 0.02066 -0.0599 0.1067 1.0000
8.750 1.1716 0.03129 0.02171 -0.0595 0.1017 1.0000
9.000 1.1900 0.03241 0.02280 -0.0588 0.0975 1.0000
9.250 1.2106 0.03349 0.02402 -0.0583 0.0931 1.0000
9.500 1.2297 0.03459 0.02521 -0.0576 0.0890 1.0000
9.750 1.2466 0.03575 0.02637 -0.0568 0.0855 1.0000
10.000 1.2646 0.03704 0.02776 -0.0560 0.0821 1.0000
10.250 1.2821 0.03830 0.02920 -0.0551 0.0785 1.0000
10.500 1.2972 0.03956 0.03055 -0.0541 0.0754 1.0000
10.750 1.3112 0.04090 0.03189 -0.0531 0.0729 1.0000
11.000 1.3258 0.04246 0.03364 -0.0520 0.0703 1.0000
11.250 1.3388 0.04406 0.03547 -0.0508 0.0676 1.0000
11.500 1.3498 0.04564 0.03719 -0.0496 0.0652 1.0000
11.750 1.3594 0.04719 0.03881 -0.0483 0.0632 1.0000
12.000 1.3700 0.04887 0.04049 -0.0472 0.0616 1.0000
12.250 1.3766 0.05110 0.04304 -0.0457 0.0599 1.0000
12.500 1.3808 0.05347 0.04570 -0.0442 0.0581 1.0000
12.750 1.3833 0.05588 0.04835 -0.0428 0.0566 1.0000
13.000 1.3848 0.05827 0.05092 -0.0416 0.0552 1.0000
13.250 1.3862 0.06063 0.05341 -0.0405 0.0540 1.0000
13.500 1.3885 0.06295 0.05580 -0.0396 0.0529 1.0000
13.750 1.3917 0.06539 0.05828 -0.0388 0.0520 1.0000
14.000 1.3799 0.06948 0.06272 -0.0379 0.0512 1.0000
14.250 1.3655 0.07408 0.06767 -0.0376 0.0505 1.0000
14.500 1.3478 0.07923 0.07315 -0.0378 0.0500 1.0000
14.750 1.3267 0.08512 0.07934 -0.0388 0.0495 1.0000
15.000 1.3012 0.09206 0.08658 -0.0410 0.0492 1.0000
15.250 1.2698 0.10074 0.09556 -0.0450 0.0491 1.0000
15.500 1.2242 0.11344 0.10859 -0.0526 0.0493 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NASA/LANGLEY LS(1)-0413 (GA(W)-2) AIRFOIL (ls413-il)