NASA/LANGLEY LS(1)-0417MOD AIRFOIL (ls417mod-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY LS(1)-0417MOD AIRFOIL (ls417mod-il) Reynolds number: 200,000 Max Cl/Cd: 57.35 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ls417mod-il-200000-n5.txt Download as CSV file: xf-ls417mod-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.250 -0.7050 0.09502 0.09019 -0.0493 1.0000 0.0230
-15.000 -0.7563 0.08087 0.07568 -0.0589 1.0000 0.0228
-14.750 -0.7859 0.07228 0.06682 -0.0643 1.0000 0.0228
-14.500 -0.8078 0.06589 0.06018 -0.0677 1.0000 0.0229
-14.250 -0.8248 0.06072 0.05477 -0.0699 1.0000 0.0230
-14.000 -0.8378 0.05640 0.05023 -0.0712 1.0000 0.0231
-13.750 -0.8477 0.05266 0.04627 -0.0719 1.0000 0.0233
-13.500 -0.8549 0.04940 0.04278 -0.0721 1.0000 0.0235
-13.250 -0.8597 0.04653 0.03968 -0.0718 1.0000 0.0237
-13.000 -0.8596 0.04423 0.03722 -0.0712 1.0000 0.0239
-12.750 -0.8539 0.04252 0.03546 -0.0704 1.0000 0.0241
-12.500 -0.8483 0.04092 0.03382 -0.0694 1.0000 0.0243
-12.250 -0.8432 0.03944 0.03228 -0.0682 1.0000 0.0246
-12.000 -0.8386 0.03805 0.03084 -0.0666 1.0000 0.0248
-11.750 -0.8351 0.03678 0.02950 -0.0646 1.0000 0.0251
-11.500 -0.8331 0.03563 0.02828 -0.0622 1.0000 0.0254
-11.250 -0.8342 0.03462 0.02722 -0.0591 1.0000 0.0258
-11.000 -0.8416 0.03383 0.02637 -0.0547 1.0000 0.0261
-10.750 -0.8327 0.03272 0.02515 -0.0533 0.9975 0.0266
-10.500 -0.8055 0.03134 0.02360 -0.0550 0.9929 0.0274
-10.250 -0.7789 0.03020 0.02248 -0.0564 0.9877 0.0280
-10.000 -0.7509 0.02911 0.02137 -0.0580 0.9827 0.0287
-9.750 -0.7216 0.02803 0.02022 -0.0595 0.9789 0.0295
-9.500 -0.6956 0.02701 0.01911 -0.0603 0.9726 0.0303
-9.250 -0.6661 0.02599 0.01802 -0.0617 0.9683 0.0311
-9.000 -0.6370 0.02502 0.01708 -0.0631 0.9639 0.0319
-8.750 -0.6103 0.02419 0.01624 -0.0639 0.9572 0.0329
-8.500 -0.5800 0.02338 0.01537 -0.0653 0.9528 0.0342
-8.250 -0.5506 0.02256 0.01452 -0.0665 0.9471 0.0355
-8.000 -0.5221 0.02178 0.01375 -0.0674 0.9393 0.0368
-7.750 -0.4892 0.02099 0.01289 -0.0691 0.9336 0.0384
-7.500 -0.4637 0.02030 0.01219 -0.0693 0.9241 0.0398
-7.250 -0.4336 0.01962 0.01149 -0.0704 0.9174 0.0417
-7.000 -0.4062 0.01902 0.01087 -0.0708 0.9093 0.0441
-6.750 -0.3785 0.01845 0.01029 -0.0713 0.9014 0.0470
-6.500 -0.3489 0.01786 0.00968 -0.0721 0.8948 0.0505
-6.250 -0.3227 0.01736 0.00918 -0.0722 0.8859 0.0548
-6.000 -0.2941 0.01684 0.00867 -0.0727 0.8788 0.0617
-5.750 -0.2656 0.01632 0.00819 -0.0733 0.8723 0.0732
-5.500 -0.2382 0.01580 0.00778 -0.0737 0.8638 0.0915
-5.250 -0.2092 0.01527 0.00735 -0.0743 0.8560 0.1181
-5.000 -0.1803 0.01472 0.00696 -0.0751 0.8483 0.1527
-4.750 -0.1511 0.01412 0.00658 -0.0760 0.8395 0.2009
-4.500 -0.1200 0.01343 0.00616 -0.0773 0.8317 0.2685
-4.250 -0.0888 0.01277 0.00584 -0.0788 0.8227 0.3452
-4.000 -0.0565 0.01206 0.00557 -0.0803 0.8131 0.4441
-3.750 -0.0280 0.01185 0.00586 -0.0802 0.8029 0.5456
-3.500 0.0004 0.01200 0.00608 -0.0797 0.7916 0.5926
-3.250 0.0296 0.01212 0.00614 -0.0795 0.7786 0.6150
-3.000 0.0598 0.01220 0.00609 -0.0796 0.7639 0.6315
-2.750 0.0877 0.01234 0.00620 -0.0791 0.7487 0.6422
-2.500 0.1170 0.01246 0.00621 -0.0790 0.7311 0.6542
-2.250 0.1437 0.01270 0.00638 -0.0781 0.7075 0.6653
-2.000 0.1722 0.01284 0.00634 -0.0778 0.6714 0.6747
-1.750 0.1959 0.01315 0.00634 -0.0763 0.6013 0.6796
-1.500 0.2185 0.01366 0.00634 -0.0750 0.5189 0.6840
-1.250 0.2449 0.01402 0.00638 -0.0748 0.4794 0.6890
-1.000 0.2745 0.01425 0.00638 -0.0754 0.4558 0.6947
-0.500 0.3257 0.01479 0.00673 -0.0739 0.4272 0.7016
-0.250 0.3525 0.01506 0.00689 -0.0736 0.4160 0.7061
0.000 0.3819 0.01522 0.00696 -0.0739 0.4061 0.7113
0.250 0.4131 0.01538 0.00698 -0.0748 0.3970 0.7163
0.500 0.4395 0.01555 0.00711 -0.0743 0.3899 0.7186
0.750 0.4665 0.01571 0.00725 -0.0740 0.3823 0.7211
1.000 0.4939 0.01590 0.00737 -0.0738 0.3752 0.7237
1.250 0.5220 0.01608 0.00748 -0.0739 0.3691 0.7263
1.500 0.5512 0.01618 0.00757 -0.0742 0.3629 0.7289
1.750 0.5805 0.01632 0.00764 -0.0746 0.3565 0.7314
2.000 0.6098 0.01651 0.00774 -0.0751 0.3508 0.7343
2.250 0.6406 0.01663 0.00782 -0.0759 0.3455 0.7371
2.500 0.6697 0.01674 0.00792 -0.0762 0.3398 0.7388
2.750 0.6969 0.01691 0.00806 -0.0761 0.3345 0.7403
3.000 0.7236 0.01714 0.00823 -0.0759 0.3297 0.7421
3.250 0.7514 0.01729 0.00841 -0.0759 0.3250 0.7441
3.500 0.7793 0.01744 0.00858 -0.0760 0.3199 0.7461
3.750 0.8072 0.01763 0.00875 -0.0761 0.3149 0.7480
4.000 0.8347 0.01787 0.00892 -0.0762 0.3105 0.7501
4.250 0.8632 0.01805 0.00912 -0.0765 0.3060 0.7522
4.500 0.8918 0.01823 0.00932 -0.0768 0.3011 0.7546
4.750 0.9202 0.01844 0.00951 -0.0771 0.2964 0.7574
5.000 0.9481 0.01870 0.00972 -0.0774 0.2921 0.7597
5.250 0.9744 0.01892 0.00998 -0.0772 0.2879 0.7613
5.500 1.0009 0.01912 0.01024 -0.0770 0.2832 0.7629
5.750 1.0269 0.01935 0.01049 -0.0768 0.2787 0.7648
6.000 1.0524 0.01962 0.01074 -0.0765 0.2745 0.7667
6.250 1.0785 0.01990 0.01104 -0.0763 0.2704 0.7689
6.500 1.1049 0.02013 0.01135 -0.0763 0.2657 0.7712
6.750 1.1308 0.02040 0.01164 -0.0761 0.2611 0.7738
7.000 1.1560 0.02073 0.01194 -0.0759 0.2570 0.7767
7.250 1.1824 0.02104 0.01229 -0.0759 0.2527 0.7795
7.500 1.2068 0.02131 0.01264 -0.0755 0.2481 0.7816
7.750 1.2299 0.02162 0.01299 -0.0748 0.2437 0.7835
8.000 1.2521 0.02200 0.01335 -0.0740 0.2398 0.7858
8.250 1.2760 0.02231 0.01377 -0.0736 0.2352 0.7882
8.500 1.2989 0.02265 0.01418 -0.0729 0.2305 0.7908
8.750 1.3204 0.02305 0.01458 -0.0722 0.2262 0.7937
9.000 1.3426 0.02346 0.01504 -0.0715 0.2220 0.7967
9.250 1.3650 0.02386 0.01552 -0.0710 0.2172 0.7997
9.500 1.3834 0.02429 0.01599 -0.0696 0.2129 0.8020
9.750 1.3997 0.02476 0.01650 -0.0680 0.2090 0.8048
10.000 1.4168 0.02519 0.01706 -0.0664 0.2045 0.8082
10.250 1.4329 0.02571 0.01764 -0.0648 0.2000 0.8119
10.500 1.4483 0.02636 0.01829 -0.0634 0.1961 0.8157
10.750 1.4671 0.02694 0.01899 -0.0624 0.1914 0.8191
11.000 1.4819 0.02759 0.01972 -0.0609 0.1869 0.8220
11.500 1.5108 0.02908 0.02137 -0.0580 0.1784 0.8290
11.750 1.5245 0.02994 0.02230 -0.0567 0.1740 0.8330
12.000 1.5364 0.03095 0.02333 -0.0554 0.1701 0.8370
12.250 1.5494 0.03184 0.02437 -0.0540 0.1657 0.8404
12.500 1.5596 0.03293 0.02554 -0.0526 0.1615 0.8444
12.750 1.5689 0.03417 0.02683 -0.0512 0.1578 0.8489
13.000 1.5802 0.03538 0.02816 -0.0502 0.1535 0.8538
13.250 1.5868 0.03679 0.02966 -0.0487 0.1496 0.8583
13.500 1.5932 0.03833 0.03128 -0.0474 0.1461 0.8635
13.750 1.6008 0.03991 0.03297 -0.0464 0.1421 0.8690
14.000 1.6042 0.04176 0.03491 -0.0453 0.1387 0.8741
14.250 1.6074 0.04372 0.03697 -0.0442 0.1354 0.8797
14.500 1.6109 0.04580 0.03918 -0.0434 0.1319 0.8858
14.750 1.6099 0.04822 0.04169 -0.0425 0.1288 0.8919
15.000 1.6086 0.05081 0.04439 -0.0419 0.1259 0.8991
15.250 1.6069 0.05348 0.04722 -0.0413 0.1227 0.9072
15.750 1.5923 0.06015 0.05409 -0.0406 0.1177 0.9333
16.250 1.5764 0.06793 0.06219 -0.0417 0.1124 1.0000
16.500 1.5661 0.07290 0.06723 -0.0434 0.1100 1.0000
16.750 1.5561 0.07795 0.07241 -0.0452 0.1076 1.0000
17.000 1.5450 0.08330 0.07791 -0.0472 0.1051 1.0000
17.250 1.5317 0.08901 0.08372 -0.0495 0.1027 1.0000
17.500 1.5184 0.09465 0.08940 -0.0518 0.1007 1.0000
17.750 1.5054 0.10038 0.09530 -0.0542 0.0982 1.0000
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Polar data table (+)
Polar graphs
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