NASA/LANGLEY LS(1)-0417MOD AIRFOIL (ls417mod-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY LS(1)-0417MOD AIRFOIL (ls417mod-il) Reynolds number: 500,000 Max Cl/Cd: 81.62 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ls417mod-il-500000-n5.txt Download as CSV file: xf-ls417mod-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.000 -0.8623 0.12900 0.12536 -0.0266 1.0000 0.0145
-18.500 -0.9175 0.10962 0.10564 -0.0377 1.0000 0.0145
-18.250 -0.9361 0.10211 0.09799 -0.0419 1.0000 0.0146
-18.000 -0.9531 0.09506 0.09082 -0.0458 1.0000 0.0146
-17.750 -0.9674 0.08864 0.08428 -0.0494 1.0000 0.0147
-17.500 -0.9798 0.08261 0.07813 -0.0527 1.0000 0.0147
-17.250 -0.9900 0.07712 0.07252 -0.0557 1.0000 0.0148
-17.000 -0.9981 0.07204 0.06733 -0.0584 1.0000 0.0149
-16.750 -1.0041 0.06742 0.06260 -0.0608 1.0000 0.0150
-16.500 -1.0081 0.06325 0.05834 -0.0629 1.0000 0.0150
-16.250 -1.0106 0.05942 0.05441 -0.0646 1.0000 0.0151
-16.000 -1.0115 0.05596 0.05086 -0.0661 1.0000 0.0152
-15.750 -1.0112 0.05282 0.04763 -0.0673 1.0000 0.0153
-15.500 -1.0096 0.04997 0.04469 -0.0682 1.0000 0.0154
-15.250 -1.0070 0.04736 0.04201 -0.0688 1.0000 0.0156
-15.000 -1.0037 0.04499 0.03956 -0.0692 1.0000 0.0157
-14.750 -0.9994 0.04281 0.03730 -0.0693 1.0000 0.0159
-14.500 -0.9943 0.04077 0.03518 -0.0694 1.0000 0.0160
-14.250 -0.9881 0.03891 0.03324 -0.0692 1.0000 0.0162
-14.000 -0.9808 0.03719 0.03145 -0.0690 1.0000 0.0164
-13.750 -0.9730 0.03559 0.02977 -0.0686 1.0000 0.0167
-13.500 -0.9642 0.03412 0.02822 -0.0680 1.0000 0.0169
-13.250 -0.9552 0.03274 0.02676 -0.0674 1.0000 0.0171
-13.000 -0.9454 0.03151 0.02545 -0.0665 1.0000 0.0173
-12.750 -0.9375 0.03022 0.02412 -0.0654 1.0000 0.0175
-12.500 -0.9311 0.02900 0.02288 -0.0640 1.0000 0.0177
-12.250 -0.9250 0.02795 0.02181 -0.0621 1.0000 0.0179
-12.000 -0.9204 0.02703 0.02087 -0.0599 1.0000 0.0181
-11.750 -0.9109 0.02611 0.01993 -0.0584 0.9987 0.0183
-11.500 -0.8861 0.02506 0.01884 -0.0598 0.9937 0.0186
-11.250 -0.8626 0.02408 0.01781 -0.0608 0.9869 0.0190
-11.000 -0.8371 0.02312 0.01680 -0.0620 0.9803 0.0194
-10.750 -0.8128 0.02222 0.01586 -0.0629 0.9715 0.0198
-10.500 -0.7842 0.02137 0.01494 -0.0644 0.9648 0.0202
-10.250 -0.7566 0.02059 0.01410 -0.0657 0.9559 0.0205
-10.000 -0.7288 0.01966 0.01316 -0.0672 0.9474 0.0210
-9.750 -0.7010 0.01894 0.01240 -0.0683 0.9372 0.0214
-9.500 -0.6741 0.01832 0.01173 -0.0690 0.9254 0.0219
-9.250 -0.6479 0.01778 0.01113 -0.0693 0.9126 0.0226
-9.000 -0.6228 0.01730 0.01058 -0.0694 0.8992 0.0232
-8.750 -0.5972 0.01686 0.01006 -0.0695 0.8886 0.0238
-8.500 -0.5721 0.01633 0.00950 -0.0696 0.8787 0.0245
-8.250 -0.5459 0.01590 0.00903 -0.0697 0.8700 0.0252
-8.000 -0.5194 0.01550 0.00858 -0.0699 0.8606 0.0259
-7.750 -0.4924 0.01514 0.00815 -0.0700 0.8526 0.0268
-7.500 -0.4649 0.01475 0.00774 -0.0703 0.8448 0.0276
-7.250 -0.4374 0.01438 0.00735 -0.0706 0.8367 0.0286
-7.000 -0.4093 0.01407 0.00699 -0.0709 0.8295 0.0299
-6.750 -0.3807 0.01375 0.00666 -0.0713 0.8224 0.0313
-6.500 -0.3521 0.01343 0.00633 -0.0717 0.8152 0.0330
-6.000 -0.2939 0.01287 0.00572 -0.0725 0.8013 0.0374
-5.750 -0.2646 0.01259 0.00544 -0.0730 0.7932 0.0412
-5.500 -0.2352 0.01233 0.00517 -0.0735 0.7853 0.0471
-5.250 -0.2052 0.01202 0.00491 -0.0741 0.7775 0.0565
-5.000 -0.1752 0.01173 0.00466 -0.0748 0.7683 0.0705
-4.750 -0.1450 0.01143 0.00442 -0.0755 0.7595 0.0896
-4.500 -0.1144 0.01111 0.00419 -0.0763 0.7488 0.1146
-4.250 -0.0836 0.01080 0.00396 -0.0772 0.7374 0.1441
-4.000 -0.0524 0.01044 0.00374 -0.0782 0.7218 0.1827
-3.750 -0.0208 0.01008 0.00351 -0.0793 0.7026 0.2307
-3.500 0.0109 0.00973 0.00328 -0.0806 0.6716 0.2924
-3.250 0.0410 0.00958 0.00307 -0.0815 0.6001 0.3520
-2.750 0.1044 0.00941 0.00305 -0.0846 0.4518 0.5599
-2.500 0.1345 0.00957 0.00317 -0.0850 0.4311 0.5947
-2.250 0.1645 0.00973 0.00323 -0.0853 0.4158 0.6105
-2.000 0.1945 0.00984 0.00330 -0.0856 0.4051 0.6211
-1.500 0.2543 0.01012 0.00347 -0.0862 0.3858 0.6424
-1.250 0.2846 0.01027 0.00351 -0.0866 0.3770 0.6501
-1.000 0.3140 0.01038 0.00358 -0.0868 0.3701 0.6547
-0.750 0.3438 0.01046 0.00364 -0.0870 0.3638 0.6582
-0.500 0.3735 0.01057 0.00369 -0.0873 0.3567 0.6611
0.000 0.4332 0.01080 0.00380 -0.0879 0.3451 0.6684
0.250 0.4634 0.01092 0.00386 -0.0883 0.3394 0.6723
0.500 0.4921 0.01103 0.00396 -0.0884 0.3335 0.6766
0.750 0.5210 0.01118 0.00408 -0.0885 0.3282 0.6806
1.000 0.5505 0.01128 0.00417 -0.0887 0.3239 0.6842
1.250 0.5799 0.01139 0.00426 -0.0890 0.3187 0.6871
1.500 0.6092 0.01153 0.00433 -0.0892 0.3134 0.6892
1.750 0.6384 0.01167 0.00442 -0.0895 0.3087 0.6912
2.000 0.6681 0.01176 0.00450 -0.0898 0.3048 0.6929
2.250 0.6975 0.01188 0.00458 -0.0901 0.3000 0.6943
2.500 0.7262 0.01200 0.00468 -0.0902 0.2953 0.6959
2.750 0.7544 0.01216 0.00480 -0.0903 0.2908 0.6977
3.000 0.7833 0.01226 0.00492 -0.0905 0.2871 0.6996
3.250 0.8120 0.01238 0.00505 -0.0906 0.2828 0.7013
3.500 0.8404 0.01253 0.00518 -0.0907 0.2784 0.7029
3.750 0.8684 0.01271 0.00533 -0.0908 0.2739 0.7045
4.000 0.8969 0.01286 0.00547 -0.0909 0.2702 0.7062
4.250 0.9254 0.01300 0.00562 -0.0910 0.2662 0.7079
4.500 0.9534 0.01317 0.00577 -0.0911 0.2617 0.7099
4.750 0.9810 0.01337 0.00594 -0.0911 0.2573 0.7120
5.000 1.0090 0.01354 0.00612 -0.0912 0.2535 0.7138
5.250 1.0370 0.01371 0.00628 -0.0913 0.2494 0.7154
5.500 1.0644 0.01390 0.00646 -0.0912 0.2450 0.7169
5.750 1.0909 0.01412 0.00668 -0.0911 0.2406 0.7187
6.000 1.1181 0.01430 0.00689 -0.0910 0.2370 0.7204
6.250 1.1450 0.01449 0.00710 -0.0909 0.2327 0.7222
6.500 1.1713 0.01472 0.00733 -0.0907 0.2283 0.7241
6.750 1.1971 0.01499 0.00758 -0.0904 0.2240 0.7260
7.000 1.2237 0.01519 0.00782 -0.0902 0.2201 0.7282
7.250 1.2496 0.01543 0.00807 -0.0900 0.2154 0.7306
7.500 1.2747 0.01573 0.00835 -0.0896 0.2110 0.7330
7.750 1.3003 0.01598 0.00862 -0.0893 0.2069 0.7352
8.000 1.3255 0.01624 0.00890 -0.0890 0.2024 0.7372
8.250 1.3495 0.01656 0.00922 -0.0885 0.1978 0.7391
8.500 1.3736 0.01685 0.00954 -0.0879 0.1937 0.7412
8.750 1.3974 0.01714 0.00987 -0.0873 0.1890 0.7434
9.000 1.4198 0.01751 0.01024 -0.0866 0.1842 0.7457
9.250 1.4426 0.01784 0.01060 -0.0858 0.1800 0.7482
9.500 1.4645 0.01819 0.01098 -0.0850 0.1751 0.7508
9.750 1.4846 0.01864 0.01141 -0.0838 0.1705 0.7534
10.000 1.5056 0.01900 0.01181 -0.0829 0.1661 0.7561
10.250 1.5232 0.01943 0.01226 -0.0813 0.1615 0.7586
10.500 1.5393 0.01990 0.01276 -0.0795 0.1574 0.7611
10.750 1.5574 0.02037 0.01328 -0.0781 0.1530 0.7638
11.000 1.5739 0.02096 0.01389 -0.0766 0.1484 0.7668
11.250 1.5915 0.02151 0.01448 -0.0752 0.1443 0.7701
11.500 1.6079 0.02214 0.01514 -0.0738 0.1398 0.7735
11.750 1.6235 0.02284 0.01586 -0.0724 0.1358 0.7767
12.000 1.6395 0.02353 0.01659 -0.0710 0.1316 0.7796
12.250 1.6529 0.02437 0.01746 -0.0695 0.1275 0.7824
12.500 1.6677 0.02514 0.01830 -0.0681 0.1238 0.7854
12.750 1.6805 0.02606 0.01927 -0.0666 0.1198 0.7887
13.000 1.6928 0.02704 0.02030 -0.0652 0.1164 0.7921
13.250 1.7050 0.02807 0.02138 -0.0638 0.1127 0.7956
13.750 1.7259 0.03046 0.02387 -0.0611 0.1060 0.8020
14.000 1.7341 0.03186 0.02533 -0.0597 0.1024 0.8054
14.250 1.7416 0.03335 0.02688 -0.0584 0.0988 0.8090
14.500 1.7478 0.03501 0.02860 -0.0572 0.0948 0.8128
14.750 1.7525 0.03686 0.03050 -0.0560 0.0911 0.8168
15.000 1.7556 0.03890 0.03259 -0.0549 0.0872 0.8205
15.250 1.7573 0.04109 0.03487 -0.0538 0.0841 0.8246
15.500 1.7589 0.04340 0.03727 -0.0530 0.0813 0.8289
15.750 1.7569 0.04616 0.04010 -0.0522 0.0790 0.8332
16.250 1.7535 0.05196 0.04612 -0.0514 0.0750 0.8413
16.500 1.7468 0.05568 0.04995 -0.0515 0.0732 0.8456
16.750 1.7389 0.05975 0.05415 -0.0519 0.0717 0.8501
17.250 1.7160 0.06948 0.06416 -0.0539 0.0687 0.8588
17.500 1.6983 0.07558 0.07041 -0.0557 0.0674 0.8633
17.750 1.6762 0.08242 0.07739 -0.0579 0.0664 0.8675
18.000 1.6578 0.08866 0.08378 -0.0599 0.0652 0.8719
18.250 1.6368 0.09528 0.09054 -0.0620 0.0641 0.8764
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