NASA/LANGLEY NLF(1)-0416 AIRFOIL (nlf416-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY NLF(1)-0416 AIRFOIL (nlf416-il) Reynolds number: 500,000 Max Cl/Cd: 91.27 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nlf416-il-500000-n5.txt Download as CSV file: xf-nlf416-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.6781 0.12034 0.11728 -0.0345 1.0000 0.0076
-16.250 -0.7310 0.10049 0.09710 -0.0449 1.0000 0.0075
-16.000 -0.7532 0.09220 0.08868 -0.0493 1.0000 0.0075
-15.750 -0.7699 0.08511 0.08146 -0.0532 1.0000 0.0075
-15.500 -0.7871 0.07824 0.07444 -0.0570 1.0000 0.0075
-15.000 -0.8115 0.06691 0.06283 -0.0631 1.0000 0.0075
-14.750 -0.8213 0.06209 0.05789 -0.0653 1.0000 0.0075
-14.250 -0.8395 0.05345 0.04898 -0.0688 1.0000 0.0076
-14.000 -0.8441 0.05017 0.04558 -0.0696 1.0000 0.0076
-13.750 -0.8499 0.04701 0.04232 -0.0700 1.0000 0.0076
-13.500 -0.8551 0.04414 0.03934 -0.0701 1.0000 0.0077
-13.250 -0.8586 0.04161 0.03672 -0.0698 1.0000 0.0078
-13.000 -0.8604 0.03939 0.03441 -0.0691 1.0000 0.0078
-12.750 -0.8609 0.03742 0.03236 -0.0682 1.0000 0.0079
-12.500 -0.8609 0.03562 0.03049 -0.0671 1.0000 0.0079
-12.250 -0.8605 0.03395 0.02875 -0.0657 1.0000 0.0080
-12.000 -0.8590 0.03249 0.02723 -0.0641 1.0000 0.0081
-11.750 -0.8578 0.03113 0.02581 -0.0623 1.0000 0.0081
-11.500 -0.8577 0.02983 0.02445 -0.0601 1.0000 0.0082
-11.250 -0.8481 0.02869 0.02326 -0.0594 0.9993 0.0084
-11.000 -0.8244 0.02736 0.02186 -0.0613 0.9966 0.0085
-10.750 -0.8007 0.02604 0.02046 -0.0633 0.9936 0.0087
-10.500 -0.7804 0.02495 0.01929 -0.0641 0.9894 0.0090
-10.250 -0.7574 0.02378 0.01804 -0.0655 0.9852 0.0092
-10.000 -0.7334 0.02263 0.01682 -0.0668 0.9806 0.0094
-9.750 -0.7099 0.02154 0.01565 -0.0679 0.9743 0.0096
-9.500 -0.6876 0.02051 0.01456 -0.0685 0.9664 0.0098
-8.750 -0.6165 0.01770 0.01159 -0.0702 0.9375 0.0105
-8.500 -0.5824 0.01688 0.01074 -0.0724 0.9281 0.0109
-8.250 -0.5401 0.01610 0.00989 -0.0761 0.9171 0.0114
-8.000 -0.4841 0.01529 0.00900 -0.0827 0.9035 0.0120
-7.750 -0.4280 0.01460 0.00818 -0.0891 0.8792 0.0127
-7.500 -0.3905 0.01407 0.00748 -0.0917 0.8411 0.0136
-7.250 -0.3645 0.01380 0.00703 -0.0918 0.8035 0.0147
-7.000 -0.3413 0.01359 0.00663 -0.0912 0.7695 0.0157
-6.750 -0.3189 0.01332 0.00624 -0.0905 0.7393 0.0175
-6.500 -0.2957 0.01310 0.00588 -0.0899 0.7131 0.0198
-6.250 -0.2715 0.01284 0.00553 -0.0896 0.6906 0.0234
-6.000 -0.2469 0.01255 0.00518 -0.0893 0.6713 0.0302
-5.750 -0.2218 0.01224 0.00485 -0.0892 0.6542 0.0430
-5.500 -0.1961 0.01192 0.00455 -0.0892 0.6388 0.0614
-5.250 -0.1700 0.01158 0.00426 -0.0893 0.6246 0.0869
-5.000 -0.1434 0.01123 0.00398 -0.0896 0.6110 0.1178
-4.750 -0.1161 0.01090 0.00374 -0.0899 0.5987 0.1509
-4.500 -0.0884 0.01050 0.00348 -0.0905 0.5877 0.1983
-4.250 -0.0599 0.01000 0.00321 -0.0913 0.5776 0.2671
-4.000 -0.0306 0.00953 0.00296 -0.0923 0.5691 0.3365
-3.750 -0.0012 0.00925 0.00278 -0.0929 0.5607 0.3805
-3.500 0.0284 0.00901 0.00262 -0.0936 0.5533 0.4237
-3.250 0.0581 0.00878 0.00249 -0.0942 0.5454 0.4701
-3.000 0.0876 0.00859 0.00242 -0.0948 0.5386 0.5165
-2.750 0.1167 0.00854 0.00251 -0.0950 0.5323 0.5596
-2.500 0.1454 0.00864 0.00260 -0.0951 0.5264 0.5870
-2.250 0.1744 0.00874 0.00266 -0.0952 0.5209 0.6028
-2.000 0.2036 0.00883 0.00270 -0.0953 0.5153 0.6141
-1.750 0.2322 0.00894 0.00276 -0.0953 0.5100 0.6220
-1.500 0.2613 0.00905 0.00278 -0.0955 0.5053 0.6300
-1.250 0.2903 0.00913 0.00283 -0.0956 0.5005 0.6351
-1.000 0.3190 0.00924 0.00290 -0.0957 0.4956 0.6397
-0.750 0.3477 0.00935 0.00294 -0.0958 0.4911 0.6446
-0.500 0.3770 0.00943 0.00296 -0.0960 0.4869 0.6489
-0.250 0.4054 0.00952 0.00305 -0.0960 0.4826 0.6520
0.000 0.4338 0.00962 0.00313 -0.0960 0.4780 0.6551
0.250 0.4622 0.00974 0.00319 -0.0961 0.4738 0.6583
0.500 0.4913 0.00981 0.00324 -0.0963 0.4699 0.6616
0.750 0.5205 0.00989 0.00327 -0.0966 0.4656 0.6646
1.000 0.5486 0.00996 0.00334 -0.0965 0.4612 0.6667
1.250 0.5765 0.01008 0.00343 -0.0965 0.4570 0.6689
1.500 0.6050 0.01015 0.00351 -0.0966 0.4531 0.6710
1.750 0.6335 0.01022 0.00359 -0.0967 0.4487 0.6730
2.000 0.6618 0.01031 0.00365 -0.0967 0.4441 0.6749
2.500 0.7187 0.01047 0.00379 -0.0970 0.4353 0.6786
2.750 0.7473 0.01056 0.00385 -0.0972 0.4303 0.6805
3.000 0.7753 0.01065 0.00393 -0.0972 0.4255 0.6820
3.250 0.8031 0.01073 0.00402 -0.0972 0.4209 0.6833
3.500 0.8312 0.01080 0.00412 -0.0972 0.4156 0.6845
3.750 0.8587 0.01090 0.00422 -0.0972 0.4099 0.6857
4.000 0.8864 0.01100 0.00433 -0.0972 0.4043 0.6868
4.250 0.9142 0.01109 0.00443 -0.0972 0.3976 0.6877
4.500 0.9412 0.01122 0.00454 -0.0971 0.3905 0.6887
4.750 0.9689 0.01131 0.00466 -0.0971 0.3829 0.6899
5.000 0.9956 0.01146 0.00479 -0.0970 0.3749 0.6910
5.250 1.0229 0.01158 0.00492 -0.0969 0.3659 0.6920
5.500 1.0494 0.01174 0.00507 -0.0968 0.3564 0.6929
5.750 1.0757 0.01192 0.00523 -0.0966 0.3453 0.6938
6.000 1.1017 0.01212 0.00540 -0.0963 0.3338 0.6947
6.250 1.1272 0.01235 0.00561 -0.0960 0.3218 0.6956
6.500 1.1521 0.01263 0.00584 -0.0956 0.3088 0.6965
6.750 1.1766 0.01293 0.00609 -0.0952 0.2959 0.6975
7.000 1.2005 0.01324 0.00638 -0.0946 0.2821 0.6985
7.250 1.2244 0.01355 0.00666 -0.0941 0.2691 0.6993
7.500 1.2479 0.01387 0.00697 -0.0935 0.2570 0.7002
7.750 1.2708 0.01423 0.00732 -0.0928 0.2449 0.7010
8.000 1.2930 0.01462 0.00768 -0.0920 0.2325 0.7018
8.500 1.3366 0.01541 0.00845 -0.0903 0.2092 0.7036
8.750 1.3575 0.01584 0.00886 -0.0893 0.1985 0.7046
9.000 1.3773 0.01630 0.00930 -0.0882 0.1878 0.7056
9.250 1.3964 0.01678 0.00977 -0.0870 0.1770 0.7066
9.500 1.4152 0.01725 0.01024 -0.0857 0.1672 0.7076
9.750 1.4311 0.01775 0.01073 -0.0839 0.1581 0.7087
10.000 1.4454 0.01828 0.01125 -0.0818 0.1490 0.7098
10.250 1.4603 0.01882 0.01181 -0.0799 0.1411 0.7110
10.500 1.4727 0.01948 0.01246 -0.0777 0.1330 0.7123
10.750 1.4863 0.02009 0.01309 -0.0758 0.1254 0.7135
11.000 1.4972 0.02084 0.01384 -0.0735 0.1179 0.7146
11.250 1.5071 0.02164 0.01466 -0.0713 0.1098 0.7157
11.500 1.5159 0.02253 0.01556 -0.0690 0.1021 0.7167
11.750 1.5216 0.02363 0.01666 -0.0665 0.0942 0.7179
12.000 1.5284 0.02472 0.01778 -0.0644 0.0873 0.7190
12.250 1.5332 0.02601 0.01910 -0.0623 0.0816 0.7203
12.500 1.5388 0.02733 0.02048 -0.0605 0.0767 0.7216
12.750 1.5414 0.02898 0.02216 -0.0587 0.0721 0.7229
13.000 1.5462 0.03059 0.02383 -0.0573 0.0681 0.7242
13.250 1.5476 0.03260 0.02589 -0.0561 0.0641 0.7256
13.500 1.5496 0.03471 0.02807 -0.0552 0.0607 0.7269
13.750 1.5511 0.03700 0.03042 -0.0545 0.0571 0.7282
14.000 1.5496 0.03971 0.03318 -0.0540 0.0539 0.7295
14.500 1.5497 0.04519 0.03883 -0.0536 0.0484 0.7320
14.750 1.5463 0.04846 0.04217 -0.0537 0.0459 0.7333
15.000 1.5453 0.05155 0.04536 -0.0540 0.0436 0.7346
15.250 1.5421 0.05497 0.04886 -0.0544 0.0412 0.7361
15.500 1.5367 0.05876 0.05272 -0.0549 0.0389 0.7376
15.750 1.5339 0.06233 0.05638 -0.0556 0.0369 0.7392
16.000 1.5296 0.06617 0.06031 -0.0564 0.0348 0.7408
16.250 1.5237 0.07035 0.06457 -0.0575 0.0330 0.7424
16.500 1.5195 0.07439 0.06870 -0.0586 0.0312 0.7440
16.750 1.5152 0.07854 0.07293 -0.0598 0.0296 0.7454
17.250 1.5041 0.08747 0.08204 -0.0627 0.0266 0.7482
17.500 1.4993 0.09198 0.08666 -0.0643 0.0252 0.7497
17.750 1.4928 0.09681 0.09157 -0.0662 0.0238 0.7512
18.000 1.4861 0.10177 0.09663 -0.0682 0.0225 0.7528
18.250 1.4815 0.10644 0.10140 -0.0701 0.0213 0.7546
18.500 1.4752 0.11149 0.10654 -0.0723 0.0201 0.7564
18.750 1.4675 0.11683 0.11198 -0.0748 0.0191 0.7581
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