NASA/LANGLEY LS(1)-0417 (GA(W)-1) AIRFOIL (ls417-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY LS(1)-0417 (GA(W)-1) AIRFOIL (ls417-il) Reynolds number: 200,000 Max Cl/Cd: 61.04 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ls417-il-200000.txt Download as CSV file: xf-ls417-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY LS(1)-0417 (GA(W)-1) 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 -0.3985 0.12006 0.11630 -0.0538 1.0000 0.0769
-12.250 -0.4214 0.11990 0.11624 -0.0488 1.0000 0.0776
-12.000 -0.7747 0.05532 0.04985 -0.0871 0.9823 0.0421
-11.750 -0.7636 0.05163 0.04600 -0.0889 0.9770 0.0418
-11.500 -0.7563 0.04791 0.04197 -0.0905 0.9713 0.0417
-11.250 -0.7438 0.04424 0.03788 -0.0928 0.9680 0.0418
-11.000 -0.7360 0.04167 0.03494 -0.0924 0.9612 0.0420
-10.750 -0.7177 0.03904 0.03192 -0.0935 0.9571 0.0422
-10.500 -0.6912 0.03652 0.02905 -0.0953 0.9546 0.0423
-10.250 -0.6598 0.03412 0.02652 -0.0972 0.9530 0.0427
-10.000 -0.6348 0.03257 0.02490 -0.0976 0.9490 0.0432
-9.750 -0.6118 0.03137 0.02363 -0.0974 0.9440 0.0438
-9.500 -0.5832 0.03008 0.02224 -0.0982 0.9409 0.0445
-9.250 -0.5528 0.02881 0.02085 -0.0992 0.9385 0.0455
-9.000 -0.5214 0.02765 0.01952 -0.1004 0.9365 0.0467
-8.750 -0.4950 0.02668 0.01849 -0.1005 0.9334 0.0481
-8.500 -0.4774 0.02612 0.01799 -0.0991 0.9276 0.0496
-8.250 -0.4517 0.02540 0.01723 -0.0992 0.9240 0.0516
-8.000 -0.4235 0.02459 0.01634 -0.0995 0.9212 0.0535
-7.750 -0.3955 0.02365 0.01553 -0.0999 0.9188 0.0558
-7.500 -0.3700 0.02302 0.01486 -0.0999 0.9158 0.0588
-7.250 -0.3572 0.02253 0.01445 -0.0980 0.9095 0.0616
-7.000 -0.3348 0.02197 0.01389 -0.0978 0.9056 0.0667
-6.750 -0.3103 0.02119 0.01319 -0.0981 0.9026 0.0746
-6.500 -0.2834 0.02033 0.01247 -0.0990 0.9002 0.0889
-6.250 -0.2551 0.01942 0.01178 -0.1002 0.8982 0.1191
-6.000 -0.2384 0.01888 0.01151 -0.0997 0.8926 0.1608
-5.750 -0.2131 0.01794 0.01106 -0.1011 0.8884 0.2453
-5.500 -0.1813 0.01694 0.01062 -0.1036 0.8858 0.3618
-5.250 -0.1488 0.01624 0.01048 -0.1056 0.8836 0.4745
-5.000 -0.1205 0.01637 0.01103 -0.1052 0.8815 0.5636
-4.750 -0.0895 0.01676 0.01143 -0.1053 0.8796 0.6078
-4.500 -0.0611 0.01731 0.01195 -0.1048 0.8772 0.6318
-4.250 -0.0446 0.01806 0.01268 -0.1030 0.8712 0.6471
-4.000 -0.0183 0.01856 0.01310 -0.1026 0.8675 0.6622
-3.750 0.0039 0.01919 0.01376 -0.1004 0.8644 0.6706
-3.500 0.0342 0.01954 0.01404 -0.1005 0.8622 0.6836
-3.250 0.0570 0.02018 0.01469 -0.0982 0.8601 0.6904
-3.000 0.0882 0.02051 0.01495 -0.0984 0.8584 0.7026
-2.750 0.0901 0.02166 0.01617 -0.0934 0.8507 0.7075
-2.500 0.1103 0.02226 0.01675 -0.0916 0.8466 0.7170
-2.250 0.1332 0.02270 0.01719 -0.0897 0.8436 0.7248
-2.000 0.1575 0.02312 0.01761 -0.0879 0.8414 0.7327
-1.750 0.1902 0.02315 0.01757 -0.0888 0.8397 0.7408
-1.500 0.2171 0.02330 0.01770 -0.0877 0.8380 0.7444
-1.250 0.2157 0.02433 0.01877 -0.0836 0.8276 0.7504
-1.000 0.2515 0.02419 0.01857 -0.0857 0.8247 0.7573
-0.750 0.2783 0.02414 0.01852 -0.0846 0.8221 0.7604
-0.500 0.3100 0.02398 0.01835 -0.0844 0.8201 0.7650
-0.250 0.3503 0.02371 0.01802 -0.0868 0.8184 0.7722
0.000 0.3502 0.02458 0.01895 -0.0825 0.8075 0.7766
0.250 0.3769 0.02448 0.01886 -0.0816 0.8040 0.7805
0.500 0.4132 0.02415 0.01851 -0.0828 0.8018 0.7851
0.750 0.4600 0.02351 0.01782 -0.0864 0.7997 0.7902
1.000 0.4775 0.02357 0.01792 -0.0843 0.7915 0.7931
1.250 0.5075 0.02299 0.01735 -0.0838 0.7853 0.7958
1.500 0.5471 0.02208 0.01641 -0.0849 0.7814 0.7987
1.750 0.5899 0.02115 0.01543 -0.0867 0.7782 0.8018
2.000 0.6146 0.02116 0.01547 -0.0868 0.7677 0.8056
2.250 0.6565 0.02038 0.01467 -0.0892 0.7623 0.8083
2.500 0.6901 0.01972 0.01398 -0.0893 0.7584 0.8103
2.750 0.7086 0.01974 0.01409 -0.0876 0.7483 0.8127
3.000 0.7437 0.01906 0.01340 -0.0883 0.7417 0.8148
3.250 0.7727 0.01867 0.01304 -0.0883 0.7318 0.8176
3.500 0.8075 0.01807 0.01241 -0.0892 0.7223 0.8204
3.750 0.8381 0.01777 0.01216 -0.0899 0.7105 0.8228
4.000 0.8759 0.01725 0.01159 -0.0917 0.6995 0.8250
4.250 0.8979 0.01696 0.01137 -0.0903 0.6846 0.8271
4.500 0.9212 0.01671 0.01116 -0.0891 0.6674 0.8294
4.750 0.9471 0.01645 0.01089 -0.0885 0.6461 0.8316
5.000 0.9705 0.01633 0.01076 -0.0876 0.6155 0.8339
5.250 0.9943 0.01629 0.01052 -0.0867 0.5668 0.8363
5.500 1.0112 0.01674 0.01054 -0.0848 0.4999 0.8389
5.750 1.0219 0.01765 0.01101 -0.0823 0.4337 0.8420
6.000 1.0234 0.01849 0.01156 -0.0778 0.3830 0.8445
6.250 1.0233 0.01935 0.01220 -0.0733 0.3394 0.8472
6.500 1.0272 0.02036 0.01299 -0.0699 0.3010 0.8500
6.750 1.0360 0.02148 0.01390 -0.0677 0.2678 0.8530
7.000 1.0482 0.02257 0.01482 -0.0662 0.2406 0.8559
7.250 1.0621 0.02370 0.01578 -0.0652 0.2195 0.8586
7.500 1.0736 0.02460 0.01662 -0.0632 0.2035 0.8611
7.750 1.0872 0.02548 0.01745 -0.0617 0.1899 0.8639
8.000 1.1011 0.02643 0.01835 -0.0603 0.1790 0.8674
8.250 1.1162 0.02745 0.01928 -0.0592 0.1697 0.8710
8.500 1.1354 0.02835 0.02019 -0.0588 0.1614 0.8744
8.750 1.1490 0.02928 0.02104 -0.0573 0.1549 0.8772
9.000 1.1656 0.03008 0.02189 -0.0561 0.1490 0.8804
9.250 1.1829 0.03091 0.02274 -0.0553 0.1437 0.8840
9.500 1.2023 0.03191 0.02362 -0.0547 0.1387 0.8876
9.750 1.2208 0.03271 0.02453 -0.0541 0.1342 0.8912
10.000 1.2363 0.03348 0.02534 -0.0529 0.1301 0.8950
10.250 1.2564 0.03437 0.02610 -0.0522 0.1259 0.8992
10.500 1.2732 0.03528 0.02716 -0.0515 0.1225 0.9041
10.750 1.2881 0.03607 0.02802 -0.0503 0.1191 0.9089
11.000 1.3046 0.03692 0.02886 -0.0493 0.1161 0.9142
11.250 1.3258 0.03788 0.02981 -0.0490 0.1128 0.9192
11.500 1.3377 0.03877 0.03087 -0.0475 0.1101 0.9249
11.750 1.3524 0.03973 0.03188 -0.0465 0.1073 0.9314
12.000 1.3671 0.04055 0.03268 -0.0453 0.1047 0.9386
12.250 1.3846 0.04151 0.03367 -0.0444 0.1021 0.9469
12.500 1.3921 0.04256 0.03491 -0.0425 0.0997 0.9594
12.750 1.4000 0.04348 0.03594 -0.0409 0.0974 1.0000
13.000 1.4198 0.04470 0.03712 -0.0413 0.0948 1.0000
13.250 1.4408 0.04612 0.03856 -0.0416 0.0921 1.0000
13.500 1.4507 0.04792 0.04057 -0.0413 0.0897 1.0000
13.750 1.4635 0.04953 0.04225 -0.0412 0.0872 1.0000
14.000 1.4821 0.05080 0.04344 -0.0414 0.0849 1.0000
14.250 1.4950 0.05268 0.04543 -0.0411 0.0827 1.0000
14.500 1.4991 0.05490 0.04787 -0.0405 0.0807 1.0000
14.750 1.5071 0.05686 0.04992 -0.0401 0.0787 1.0000
15.000 1.5211 0.05834 0.05136 -0.0400 0.0768 1.0000
15.250 1.5343 0.06024 0.05328 -0.0397 0.0749 1.0000
15.500 1.5301 0.06316 0.05647 -0.0389 0.0734 1.0000
15.750 1.5291 0.06593 0.05943 -0.0383 0.0718 1.0000
16.000 1.5328 0.06830 0.06188 -0.0380 0.0703 1.0000
16.250 1.5447 0.06995 0.06349 -0.0379 0.0689 1.0000
16.500 1.5543 0.07216 0.06573 -0.0375 0.0675 1.0000
16.750 1.5405 0.07639 0.07027 -0.0372 0.0666 1.0000
17.000 1.5295 0.08057 0.07471 -0.0373 0.0656 1.0000
17.250 1.5215 0.08454 0.07887 -0.0376 0.0646 1.0000
17.500 1.5146 0.08847 0.08297 -0.0382 0.0636 1.0000
17.750 1.5121 0.09191 0.08651 -0.0389 0.0627 1.0000
18.000 1.5219 0.09378 0.08833 -0.0391 0.0616 1.0000
18.250 1.5236 0.09689 0.09148 -0.0395 0.0607 1.0000
18.500 1.4945 0.10426 0.09921 -0.0423 0.0603 1.0000
18.750 1.4630 0.11265 0.10793 -0.0462 0.0599 1.0000
19.000 1.4250 0.12287 0.11852 -0.0518 0.0597 1.0000
19.250 1.3677 0.13792 0.13399 -0.0617 0.0597 1.0000
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Polar data table (+)
Polar graphs
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