NASA/LANGLEY LS(1)-0417MOD AIRFOIL (ls417mod-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY LS(1)-0417MOD AIRFOIL (ls417mod-il) Reynolds number: 200,000 Max Cl/Cd: 52.51 at α=10.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ls417mod-il-200000.txt Download as CSV file: xf-ls417mod-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.6695 0.07181 0.06721 -0.0701 1.0000 0.0484
-12.250 -0.6587 0.06941 0.06487 -0.0699 1.0000 0.0488
-12.000 -0.7845 0.05807 0.05272 -0.0690 1.0000 0.0435
-11.750 -0.7939 0.05560 0.05021 -0.0664 1.0000 0.0433
-11.500 -0.8073 0.05338 0.04792 -0.0631 1.0000 0.0432
-11.250 -0.8199 0.05114 0.04559 -0.0598 1.0000 0.0430
-11.000 -0.8336 0.04916 0.04351 -0.0558 1.0000 0.0429
-10.750 -0.8477 0.04728 0.04149 -0.0514 1.0000 0.0427
-10.500 -0.8592 0.04528 0.03931 -0.0475 1.0000 0.0425
-10.250 -0.8661 0.04311 0.03691 -0.0441 1.0000 0.0424
-10.000 -0.8677 0.04087 0.03440 -0.0414 1.0000 0.0423
-9.750 -0.8505 0.03812 0.03128 -0.0418 0.9980 0.0425
-9.500 -0.8235 0.03551 0.02827 -0.0435 0.9948 0.0429
-9.250 -0.7932 0.03338 0.02567 -0.0454 0.9922 0.0435
-9.000 -0.7636 0.03185 0.02426 -0.0464 0.9892 0.0446
-8.750 -0.7321 0.03073 0.02311 -0.0479 0.9857 0.0460
-8.500 -0.6997 0.02942 0.02156 -0.0495 0.9828 0.0475
-8.250 -0.6652 0.02806 0.02003 -0.0512 0.9805 0.0487
-8.000 -0.6322 0.02697 0.01900 -0.0525 0.9767 0.0500
-7.750 -0.5974 0.02596 0.01797 -0.0540 0.9718 0.0516
-7.500 -0.5576 0.02490 0.01682 -0.0564 0.9683 0.0538
-7.250 -0.5170 0.02396 0.01598 -0.0591 0.9658 0.0565
-7.000 -0.4883 0.02323 0.01518 -0.0594 0.9595 0.0589
-6.750 -0.4533 0.02226 0.01436 -0.0612 0.9554 0.0617
-6.500 -0.4130 0.02132 0.01345 -0.0639 0.9525 0.0657
-6.250 -0.3697 0.02038 0.01257 -0.0674 0.9504 0.0717
-6.000 -0.3444 0.01973 0.01197 -0.0675 0.9430 0.0777
-5.750 -0.3054 0.01866 0.01106 -0.0704 0.9392 0.0896
-5.500 -0.2637 0.01729 0.01001 -0.0742 0.9363 0.1276
-5.250 -0.2205 0.01545 0.00893 -0.0792 0.9339 0.2492
-5.000 -0.1882 0.01430 0.00838 -0.0814 0.9264 0.3712
-4.750 -0.1498 0.01340 0.00811 -0.0839 0.9211 0.4928
-4.500 -0.1146 0.01340 0.00843 -0.0844 0.9166 0.5726
-4.250 -0.0848 0.01362 0.00863 -0.0841 0.9087 0.6108
-4.000 -0.0550 0.01396 0.00897 -0.0832 0.9007 0.6358
-3.750 -0.0251 0.01441 0.00939 -0.0821 0.8937 0.6560
-3.500 0.0010 0.01482 0.00973 -0.0807 0.8832 0.6729
-3.250 0.0248 0.01532 0.01024 -0.0779 0.8757 0.6799
-3.000 0.0501 0.01562 0.01049 -0.0765 0.8650 0.6916
-2.750 0.0753 0.01585 0.01068 -0.0746 0.8558 0.6984
-2.500 0.0964 0.01624 0.01107 -0.0717 0.8447 0.7049
-2.250 0.1257 0.01635 0.01106 -0.0712 0.8332 0.7173
-2.000 0.1429 0.01676 0.01150 -0.0671 0.8196 0.7225
-1.750 0.1664 0.01694 0.01160 -0.0648 0.8064 0.7292
-1.500 0.1980 0.01674 0.01128 -0.0657 0.7882 0.7390
-1.250 0.2192 0.01672 0.01121 -0.0631 0.7671 0.7423
-1.000 0.2419 0.01670 0.01108 -0.0610 0.7401 0.7463
-0.750 0.2662 0.01665 0.01088 -0.0597 0.6958 0.7521
-0.500 0.2954 0.01667 0.01041 -0.0602 0.6034 0.7601
-0.250 0.3099 0.01713 0.01040 -0.0567 0.5355 0.7634
0.000 0.3290 0.01756 0.01054 -0.0545 0.5036 0.7676
0.250 0.3537 0.01789 0.01064 -0.0539 0.4831 0.7732
0.500 0.3887 0.01811 0.01066 -0.0563 0.4665 0.7802
0.750 0.4091 0.01823 0.01072 -0.0543 0.4549 0.7832
1.000 0.4321 0.01843 0.01081 -0.0530 0.4441 0.7865
1.250 0.4586 0.01862 0.01091 -0.0528 0.4347 0.7904
1.500 0.4887 0.01873 0.01095 -0.0536 0.4255 0.7946
1.750 0.5236 0.01905 0.01106 -0.0558 0.4164 0.7989
2.000 0.5496 0.01902 0.01107 -0.0554 0.4092 0.8017
2.250 0.5744 0.01910 0.01114 -0.0547 0.4021 0.8042
2.500 0.6015 0.01935 0.01126 -0.0547 0.3952 0.8067
2.750 0.6298 0.01948 0.01140 -0.0549 0.3888 0.8097
3.000 0.6599 0.01958 0.01149 -0.0557 0.3821 0.8126
3.250 0.6919 0.01976 0.01160 -0.0570 0.3759 0.8150
3.500 0.7263 0.02011 0.01185 -0.0590 0.3696 0.8180
3.750 0.7533 0.02015 0.01195 -0.0590 0.3639 0.8202
4.000 0.7797 0.02025 0.01205 -0.0588 0.3582 0.8221
4.250 0.8074 0.02045 0.01219 -0.0589 0.3529 0.8240
4.500 0.8360 0.02076 0.01248 -0.0594 0.3477 0.8260
4.750 0.8640 0.02089 0.01268 -0.0596 0.3423 0.8287
5.000 0.8934 0.02107 0.01286 -0.0603 0.3368 0.8316
5.250 0.9248 0.02135 0.01306 -0.0614 0.3317 0.8339
5.500 0.9570 0.02173 0.01345 -0.0628 0.3266 0.8361
5.750 0.9840 0.02186 0.01365 -0.0630 0.3212 0.8380
6.000 1.0100 0.02200 0.01381 -0.0628 0.3163 0.8399
6.250 1.0367 0.02226 0.01402 -0.0628 0.3117 0.8422
6.500 1.0632 0.02263 0.01443 -0.0628 0.3069 0.8450
6.750 1.0898 0.02283 0.01473 -0.0629 0.3017 0.8479
7.000 1.1184 0.02305 0.01496 -0.0634 0.2967 0.8504
7.250 1.1491 0.02343 0.01524 -0.0645 0.2921 0.8529
7.500 1.1757 0.02378 0.01569 -0.0647 0.2872 0.8552
7.750 1.1988 0.02397 0.01599 -0.0640 0.2822 0.8575
8.000 1.2236 0.02417 0.01619 -0.0637 0.2775 0.8601
8.250 1.2513 0.02463 0.01655 -0.0640 0.2729 0.8630
8.500 1.2741 0.02492 0.01703 -0.0635 0.2681 0.8665
8.750 1.3002 0.02521 0.01738 -0.0637 0.2629 0.8700
9.000 1.3241 0.02544 0.01758 -0.0633 0.2584 0.8728
9.250 1.3469 0.02589 0.01807 -0.0628 0.2539 0.8758
9.500 1.3670 0.02619 0.01853 -0.0618 0.2488 0.8792
9.750 1.3903 0.02648 0.01883 -0.0614 0.2440 0.8829
10.000 1.4181 0.02702 0.01927 -0.0620 0.2394 0.8864
10.250 1.4322 0.02734 0.01982 -0.0600 0.2346 0.8900
10.500 1.4502 0.02764 0.02020 -0.0587 0.2298 0.8941
10.750 1.4728 0.02805 0.02053 -0.0583 0.2254 0.8985
11.000 1.4882 0.02860 0.02124 -0.0567 0.2206 0.9032
11.250 1.5005 0.02898 0.02173 -0.0545 0.2160 0.9087
11.500 1.5169 0.02939 0.02212 -0.0531 0.2118 0.9144
11.750 1.5282 0.02998 0.02280 -0.0509 0.2075 0.9199
12.000 1.5369 0.03059 0.02357 -0.0485 0.2029 0.9266
12.250 1.5491 0.03112 0.02412 -0.0467 0.1988 0.9334
12.500 1.5618 0.03185 0.02486 -0.0450 0.1946 0.9415
12.750 1.5657 0.03265 0.02585 -0.0423 0.1903 0.9520
13.000 1.5733 0.03331 0.02658 -0.0401 0.1862 0.9674
13.250 1.5868 0.03418 0.02742 -0.0392 0.1821 1.0000
13.500 1.5949 0.03565 0.02910 -0.0385 0.1774 1.0000
13.750 1.6080 0.03689 0.03036 -0.0383 0.1731 1.0000
14.000 1.6204 0.03835 0.03185 -0.0380 0.1689 1.0000
14.250 1.6260 0.04017 0.03384 -0.0374 0.1645 1.0000
14.500 1.6365 0.04167 0.03534 -0.0371 0.1606 1.0000
14.750 1.6427 0.04363 0.03738 -0.0367 0.1566 1.0000
15.000 1.6447 0.04588 0.03977 -0.0362 0.1527 1.0000
15.250 1.6522 0.04770 0.04158 -0.0360 0.1491 1.0000
15.500 1.6532 0.05019 0.04417 -0.0356 0.1456 1.0000
15.750 1.6504 0.05306 0.04719 -0.0354 0.1420 1.0000
16.000 1.6538 0.05533 0.04947 -0.0352 0.1388 1.0000
16.250 1.6531 0.05815 0.05235 -0.0352 0.1356 1.0000
16.500 1.6442 0.06199 0.05639 -0.0356 0.1325 1.0000
16.750 1.6432 0.06499 0.05942 -0.0360 0.1294 1.0000
17.000 1.6437 0.06787 0.06229 -0.0363 0.1263 1.0000
17.250 1.6277 0.07312 0.06778 -0.0378 0.1235 1.0000
17.500 1.6219 0.07713 0.07187 -0.0390 0.1205 1.0000
17.750 1.6265 0.07957 0.07423 -0.0395 0.1175 1.0000
18.000 1.6034 0.08643 0.08136 -0.0423 0.1150 1.0000
18.250 1.5923 0.09158 0.08664 -0.0445 0.1123 1.0000
18.500 1.6021 0.09324 0.08817 -0.0448 0.1094 1.0000
18.750 1.5775 0.10075 0.09594 -0.0484 0.1072 1.0000
19.000 1.5593 0.10730 0.10266 -0.0517 0.1047 1.0000
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Polar data table (+)
Polar graphs
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