NASA/LANGLEY LS(1)-0417MOD AIRFOIL (ls417mod-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY LS(1)-0417MOD AIRFOIL (ls417mod-il) Reynolds number: 50,000 Max Cl/Cd: 24.32 at α=3.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ls417mod-il-50000.txt Download as CSV file: xf-ls417mod-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY LS(1)-0417MOD AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4771 0.09203 0.08484 -0.0483 1.0000 0.1609
-9.750 -0.4697 0.08812 0.08095 -0.0477 1.0000 0.1577
-9.500 -0.5706 0.07799 0.07088 -0.0503 1.0000 0.1449
-9.250 -0.5953 0.07443 0.06737 -0.0481 1.0000 0.1426
-9.000 -0.6325 0.07044 0.06331 -0.0456 1.0000 0.1397
-8.750 -0.7024 0.06493 0.05714 -0.0425 1.0000 0.1339
-8.500 -0.7027 0.06154 0.05363 -0.0407 1.0000 0.1329
-8.250 -0.7046 0.05811 0.04996 -0.0391 1.0000 0.1323
-8.000 -0.7042 0.05472 0.04622 -0.0378 1.0000 0.1324
-7.750 -0.6993 0.05145 0.04249 -0.0368 1.0000 0.1332
-7.500 -0.6888 0.04840 0.03898 -0.0362 1.0000 0.1343
-7.250 -0.6719 0.04602 0.03663 -0.0352 1.0000 0.1366
-7.000 -0.6543 0.04369 0.03409 -0.0344 1.0000 0.1386
-6.750 -0.6352 0.04158 0.03172 -0.0337 1.0000 0.1420
-6.500 -0.6144 0.03960 0.02926 -0.0334 1.0000 0.1469
-6.250 -0.5938 0.03798 0.02780 -0.0323 1.0000 0.1527
-6.000 -0.5708 0.03645 0.02597 -0.0316 1.0000 0.1595
-5.750 -0.5493 0.03512 0.02481 -0.0304 1.0000 0.1688
-5.500 -0.5276 0.03391 0.02369 -0.0291 1.0000 0.1811
-5.250 -0.5067 0.03282 0.02274 -0.0274 1.0000 0.1980
-5.000 -0.4859 0.03166 0.02177 -0.0258 1.0000 0.2263
-4.750 -0.4657 0.02999 0.02076 -0.0249 1.0000 0.2833
-4.500 -0.4538 0.02788 0.02084 -0.0213 1.0000 0.4742
-4.250 -0.4547 0.03055 0.02401 -0.0107 1.0000 0.5919
-4.000 -0.4494 0.03306 0.02642 -0.0027 1.0000 0.6449
-3.750 -0.4448 0.03517 0.02845 0.0053 1.0000 0.6799
-3.500 -0.4380 0.03675 0.02992 0.0118 1.0000 0.7165
-3.250 -0.4338 0.03814 0.03127 0.0199 1.0000 0.7435
-3.000 -0.4268 0.03901 0.03205 0.0263 1.0000 0.7748
-2.750 -0.4176 0.03943 0.03238 0.0318 1.0000 0.8053
-2.500 -0.4078 0.03948 0.03232 0.0360 1.0000 0.8370
-2.250 -0.3861 0.03952 0.03223 0.0387 1.0000 0.8678
-2.000 -0.3532 0.03952 0.03209 0.0385 1.0000 0.9011
-1.750 -0.1958 0.04065 0.03278 0.0159 0.9919 0.9417
-1.500 -0.0269 0.04044 0.03219 -0.0114 0.9670 0.9655
-1.250 0.1235 0.03909 0.03061 -0.0353 0.9388 0.9845
-1.000 0.2746 0.03674 0.02809 -0.0587 0.9103 1.0000
-0.750 0.3640 0.03457 0.02583 -0.0700 0.8795 1.0000
-0.500 0.4262 0.03271 0.02389 -0.0755 0.8437 1.0000
-0.250 0.4744 0.03106 0.02211 -0.0780 0.8100 1.0000
0.000 0.4994 0.03032 0.02124 -0.0768 0.7721 1.0000
0.250 0.5258 0.02952 0.02027 -0.0758 0.7428 1.0000
0.500 0.5461 0.02920 0.01980 -0.0744 0.7147 1.0000
0.750 0.5659 0.02901 0.01948 -0.0730 0.6899 1.0000
1.000 0.5863 0.02885 0.01918 -0.0719 0.6687 1.0000
1.250 0.6074 0.02874 0.01893 -0.0708 0.6504 1.0000
1.500 0.6297 0.02862 0.01864 -0.0699 0.6343 1.0000
1.750 0.6478 0.02890 0.01887 -0.0689 0.6177 1.0000
2.000 0.6666 0.02921 0.01911 -0.0679 0.6033 1.0000
2.250 0.6899 0.02929 0.01902 -0.0672 0.5914 1.0000
2.500 0.7060 0.02988 0.01964 -0.0661 0.5783 1.0000
2.750 0.7260 0.03029 0.01997 -0.0652 0.5674 1.0000
3.000 0.7429 0.03090 0.02058 -0.0641 0.5564 1.0000
3.250 0.7619 0.03149 0.02110 -0.0631 0.5472 1.0000
3.500 0.7743 0.03239 0.02208 -0.0614 0.5371 1.0000
3.750 0.7982 0.03282 0.02235 -0.0609 0.5288 1.0000
4.000 0.8006 0.03426 0.02402 -0.0582 0.5201 1.0000
4.250 0.8159 0.03506 0.02480 -0.0567 0.5119 1.0000
4.500 0.8294 0.03608 0.02582 -0.0551 0.5047 1.0000
4.750 0.8238 0.03786 0.02780 -0.0514 0.4975 1.0000
5.000 0.8346 0.03888 0.02884 -0.0494 0.4904 1.0000
5.250 0.8519 0.03981 0.02972 -0.0480 0.4840 1.0000
5.500 0.8192 0.04258 0.03279 -0.0414 0.4787 1.0000
5.750 0.7845 0.04542 0.03582 -0.0348 0.4737 1.0000
6.000 0.7797 0.04725 0.03770 -0.0317 0.4680 1.0000
6.250 0.8237 0.04738 0.03771 -0.0331 0.4612 1.0000
6.500 0.6829 0.05979 0.05055 -0.0257 0.4584 1.0000
6.750 0.5957 0.07395 0.06487 -0.0304 0.4583 1.0000
7.000 0.5794 0.08041 0.07139 -0.0334 0.4581 1.0000
7.250 0.5784 0.08564 0.07668 -0.0361 0.4594 1.0000
7.500 0.5879 0.09027 0.08137 -0.0388 0.4609 1.0000
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Polar data table (+)
Polar graphs
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