NASA/LANGLEY NLF(1)-0416 AIRFOIL (nlf416-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY NLF(1)-0416 AIRFOIL (nlf416-il) Reynolds number: 100,000 Max Cl/Cd: 45.13 at α=10.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nlf416-il-100000.txt Download as CSV file: xf-nlf416-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY NLF(1)-0416 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4638 0.08754 0.08257 -0.0553 1.0000 0.0730
-10.500 -0.5675 0.07190 0.06672 -0.0654 1.0000 0.0645
-10.250 -0.5730 0.06821 0.06301 -0.0648 1.0000 0.0622
-10.000 -0.5920 0.06461 0.05939 -0.0638 1.0000 0.0613
-9.750 -0.6179 0.06169 0.05643 -0.0615 1.0000 0.0604
-9.500 -0.6430 0.05854 0.05318 -0.0592 1.0000 0.0593
-9.250 -0.6676 0.05464 0.04903 -0.0568 1.0000 0.0578
-9.000 -0.7065 0.05050 0.04395 -0.0532 1.0000 0.0543
-8.750 -0.7014 0.04728 0.04057 -0.0516 1.0000 0.0538
-8.500 -0.6984 0.04454 0.03753 -0.0498 1.0000 0.0539
-8.250 -0.6931 0.04205 0.03469 -0.0482 1.0000 0.0543
-8.000 -0.6831 0.03915 0.03163 -0.0469 1.0000 0.0550
-7.750 -0.6710 0.03705 0.02944 -0.0456 1.0000 0.0560
-7.500 -0.6578 0.03515 0.02737 -0.0441 1.0000 0.0566
-7.250 -0.6437 0.03343 0.02548 -0.0427 1.0000 0.0572
-7.000 -0.6292 0.03199 0.02391 -0.0412 1.0000 0.0581
-6.750 -0.6094 0.03066 0.02244 -0.0406 0.9987 0.0596
-6.500 -0.5611 0.02902 0.02053 -0.0444 0.9901 0.0631
-6.250 -0.5154 0.02742 0.01911 -0.0481 0.9812 0.0703
-6.000 -0.4699 0.02585 0.01765 -0.0516 0.9716 0.0804
-5.750 -0.4274 0.02411 0.01611 -0.0549 0.9599 0.1026
-5.500 -0.3879 0.02127 0.01422 -0.0593 0.9475 0.2077
-5.250 -0.3451 0.01921 0.01318 -0.0643 0.9346 0.3755
-5.000 -0.3062 0.01878 0.01341 -0.0657 0.9211 0.4929
-4.750 -0.2689 0.01989 0.01472 -0.0644 0.9076 0.5575
-4.500 -0.2201 0.02127 0.01592 -0.0651 0.8994 0.5936
-4.250 -0.1788 0.02233 0.01679 -0.0653 0.8854 0.6185
-4.000 -0.1395 0.02338 0.01766 -0.0646 0.8717 0.6356
-3.750 -0.0991 0.02417 0.01828 -0.0644 0.8582 0.6517
-3.500 -0.0583 0.02472 0.01863 -0.0646 0.8449 0.6673
-3.250 -0.0182 0.02508 0.01879 -0.0651 0.8315 0.6827
-3.000 0.0155 0.02535 0.01887 -0.0650 0.8160 0.6980
-2.750 0.0460 0.02574 0.01912 -0.0630 0.8007 0.7066
-2.500 0.0732 0.02583 0.01906 -0.0619 0.7859 0.7199
-2.250 0.0988 0.02585 0.01892 -0.0610 0.7727 0.7337
-2.000 0.1255 0.02582 0.01872 -0.0604 0.7612 0.7477
-1.750 0.1524 0.02581 0.01859 -0.0591 0.7496 0.7581
-1.500 0.1752 0.02573 0.01842 -0.0577 0.7385 0.7695
-1.250 0.2019 0.02559 0.01811 -0.0574 0.7299 0.7819
-1.000 0.2168 0.02555 0.01803 -0.0555 0.7193 0.7947
-0.750 0.2491 0.02534 0.01767 -0.0553 0.7114 0.8031
-0.500 0.2649 0.02522 0.01753 -0.0535 0.7020 0.8137
0.000 0.3100 0.02494 0.01712 -0.0517 0.6863 0.8320
0.250 0.3301 0.02487 0.01694 -0.0509 0.6796 0.8417
0.500 0.3533 0.02471 0.01679 -0.0499 0.6717 0.8486
0.750 0.3697 0.02469 0.01671 -0.0486 0.6649 0.8570
1.000 0.3983 0.02451 0.01648 -0.0486 0.6584 0.8631
1.250 0.4112 0.02456 0.01654 -0.0466 0.6510 0.8704
1.500 0.4404 0.02439 0.01628 -0.0470 0.6450 0.8758
1.750 0.4559 0.02446 0.01641 -0.0453 0.6378 0.8816
2.000 0.4727 0.02452 0.01645 -0.0441 0.6312 0.8871
2.250 0.5031 0.02442 0.01627 -0.0446 0.6255 0.8913
2.500 0.5158 0.02459 0.01653 -0.0426 0.6179 0.8962
2.750 0.5398 0.02461 0.01649 -0.0424 0.6118 0.9004
3.000 0.5588 0.02475 0.01668 -0.0414 0.6051 0.9041
3.250 0.5799 0.02484 0.01681 -0.0407 0.5978 0.9079
3.500 0.6121 0.02483 0.01669 -0.0417 0.5924 0.9114
3.750 0.6206 0.02525 0.01726 -0.0394 0.5842 0.9151
4.000 0.6495 0.02522 0.01719 -0.0398 0.5777 0.9180
4.250 0.6692 0.02551 0.01756 -0.0390 0.5704 0.9211
4.500 0.6930 0.02565 0.01773 -0.0388 0.5627 0.9241
4.750 0.7232 0.02575 0.01778 -0.0394 0.5565 0.9270
5.000 0.7384 0.02618 0.01835 -0.0382 0.5476 0.9298
5.250 0.7746 0.02606 0.01816 -0.0396 0.5415 0.9321
5.500 0.7869 0.02661 0.01888 -0.0379 0.5320 0.9352
5.750 0.8227 0.02649 0.01871 -0.0393 0.5252 0.9374
6.000 0.8376 0.02707 0.01945 -0.0380 0.5159 0.9406
6.250 0.8730 0.02693 0.01926 -0.0393 0.5086 0.9431
6.500 0.8902 0.02748 0.01996 -0.0384 0.4989 0.9457
6.750 0.9279 0.02725 0.01969 -0.0399 0.4913 0.9477
7.000 0.9444 0.02780 0.02040 -0.0389 0.4810 0.9512
7.250 0.9855 0.02741 0.01993 -0.0408 0.4735 0.9540
7.500 0.9998 0.02802 0.02075 -0.0396 0.4624 0.9578
7.750 1.0346 0.02791 0.02063 -0.0408 0.4536 0.9604
8.000 1.0612 0.02804 0.02087 -0.0411 0.4431 0.9640
8.250 1.0855 0.02832 0.02127 -0.0411 0.4323 0.9685
8.500 1.1289 0.02782 0.02066 -0.0434 0.4233 0.9725
8.750 1.1498 0.02822 0.02129 -0.0432 0.4106 0.9811
9.000 1.1756 0.02843 0.02160 -0.0436 0.3989 1.0000
9.250 1.2078 0.02826 0.02141 -0.0445 0.3880 1.0000
9.500 1.2370 0.02821 0.02137 -0.0450 0.3761 1.0000
9.750 1.2569 0.02859 0.02189 -0.0446 0.3631 1.0000
10.000 1.2798 0.02890 0.02227 -0.0445 0.3502 1.0000
10.250 1.3040 0.02919 0.02258 -0.0446 0.3373 1.0000
10.500 1.3285 0.02953 0.02292 -0.0447 0.3241 1.0000
10.750 1.3524 0.02997 0.02332 -0.0448 0.3106 1.0000
11.000 1.3758 0.03055 0.02382 -0.0449 0.2969 1.0000
11.250 1.3872 0.03150 0.02489 -0.0435 0.2839 1.0000
11.500 1.3983 0.03257 0.02606 -0.0422 0.2713 1.0000
11.750 1.4111 0.03369 0.02721 -0.0413 0.2592 1.0000
12.000 1.4259 0.03481 0.02830 -0.0406 0.2472 1.0000
12.250 1.4436 0.03591 0.02928 -0.0403 0.2350 1.0000
12.500 1.4416 0.03766 0.03125 -0.0382 0.2251 1.0000
12.750 1.4490 0.03930 0.03294 -0.0373 0.2150 1.0000
13.000 1.4641 0.04067 0.03419 -0.0370 0.2043 1.0000
13.250 1.4579 0.04299 0.03674 -0.0355 0.1960 1.0000
13.500 1.4654 0.04489 0.03864 -0.0350 0.1870 1.0000
13.750 1.4679 0.04700 0.04079 -0.0344 0.1784 1.0000
14.000 1.4663 0.04966 0.04357 -0.0339 0.1710 1.0000
14.250 1.4760 0.05149 0.04531 -0.0338 0.1624 1.0000
14.500 1.4654 0.05501 0.04909 -0.0335 0.1564 1.0000
14.750 1.4733 0.05703 0.05102 -0.0336 0.1486 1.0000
15.000 1.4627 0.06091 0.05513 -0.0338 0.1432 1.0000
15.250 1.4597 0.06403 0.05832 -0.0343 0.1369 1.0000
15.500 1.4597 0.06717 0.06149 -0.0347 0.1309 1.0000
15.750 1.4450 0.07181 0.06638 -0.0358 0.1263 1.0000
16.000 1.4583 0.07350 0.06789 -0.0359 0.1190 1.0000
16.250 1.4349 0.07949 0.07422 -0.0378 0.1160 1.0000
16.500 1.4251 0.08400 0.07886 -0.0394 0.1114 1.0000
16.750 1.4320 0.08653 0.08131 -0.0399 0.1055 1.0000
17.000 1.4063 0.09362 0.08872 -0.0429 0.1032 1.0000
17.250 1.3879 0.09993 0.09524 -0.0458 0.1001 1.0000
17.500 1.4050 0.10087 0.09601 -0.0457 0.0937 1.0000
17.750 1.3744 0.10948 0.10493 -0.0501 0.0923 1.0000
18.000 1.3385 0.11956 0.11533 -0.0558 0.0916 1.0000
18.250 1.2833 0.13423 0.13032 -0.0647 0.0927 1.0000
18.500 1.3454 0.12592 0.12166 -0.0589 0.0827 1.0000
18.750 1.3028 0.13822 0.13424 -0.0666 0.0829 1.0000
19.000 0.9931 0.23535 0.23126 -0.1276 0.1376 1.0000
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Polar data table (+)
Polar graphs
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