NASA/LANGLEY NLF(1)-0416 AIRFOIL (nlf416-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY NLF(1)-0416 AIRFOIL (nlf416-il) Reynolds number: 50,000 Max Cl/Cd: 25.73 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nlf416-il-50000-n5.txt Download as CSV file: xf-nlf416-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.4517 0.10417 0.09665 -0.0488 1.0000 0.0457
-11.750 -0.4649 0.09707 0.08957 -0.0522 1.0000 0.0453
-11.500 -0.4845 0.08935 0.08186 -0.0563 1.0000 0.0449
-11.250 -0.5069 0.08219 0.07467 -0.0601 1.0000 0.0444
-11.000 -0.5321 0.07582 0.06822 -0.0632 1.0000 0.0439
-10.750 -0.5570 0.07050 0.06280 -0.0650 1.0000 0.0436
-10.500 -0.5798 0.06617 0.05836 -0.0655 1.0000 0.0435
-10.250 -0.6004 0.06257 0.05464 -0.0649 1.0000 0.0433
-10.000 -0.6205 0.05959 0.05152 -0.0632 1.0000 0.0435
-9.750 -0.6385 0.05697 0.04877 -0.0609 1.0000 0.0437
-9.500 -0.6494 0.05421 0.04581 -0.0591 1.0000 0.0441
-9.250 -0.6567 0.05148 0.04282 -0.0571 1.0000 0.0449
-9.000 -0.6597 0.04892 0.03991 -0.0551 1.0000 0.0458
-8.750 -0.6534 0.04692 0.03786 -0.0534 1.0000 0.0469
-8.500 -0.6455 0.04517 0.03605 -0.0517 1.0000 0.0483
-8.250 -0.6364 0.04335 0.03409 -0.0499 1.0000 0.0499
-8.000 -0.6250 0.04157 0.03213 -0.0480 1.0000 0.0513
-7.750 -0.6118 0.03994 0.03028 -0.0460 1.0000 0.0531
-7.500 -0.5992 0.03858 0.02888 -0.0440 1.0000 0.0555
-7.250 -0.5887 0.03750 0.02783 -0.0420 1.0000 0.0588
-7.000 -0.5764 0.03649 0.02665 -0.0398 1.0000 0.0629
-6.750 -0.5666 0.03553 0.02578 -0.0375 1.0000 0.0667
-6.500 -0.5358 0.03435 0.02452 -0.0387 0.9931 0.0756
-6.250 -0.4990 0.03286 0.02312 -0.0416 0.9814 0.0904
-6.000 -0.4665 0.03118 0.02162 -0.0442 0.9675 0.1162
-5.750 -0.4371 0.02926 0.02010 -0.0468 0.9521 0.1637
-5.500 -0.4079 0.02736 0.01875 -0.0497 0.9364 0.2431
-5.250 -0.3781 0.02590 0.01789 -0.0519 0.9212 0.3419
-5.000 -0.3483 0.02553 0.01803 -0.0518 0.9064 0.4305
-4.750 -0.3168 0.02624 0.01895 -0.0499 0.8922 0.4933
-4.500 -0.2807 0.02722 0.01982 -0.0488 0.8795 0.5371
-4.000 -0.2065 0.02865 0.02072 -0.0491 0.8523 0.5980
-3.750 -0.1721 0.02912 0.02092 -0.0492 0.8381 0.6206
-3.500 -0.1380 0.02945 0.02101 -0.0492 0.8245 0.6404
-3.250 -0.1034 0.02962 0.02091 -0.0496 0.8118 0.6587
-3.000 -0.0699 0.02972 0.02076 -0.0497 0.7992 0.6744
-2.750 -0.0417 0.02976 0.02060 -0.0492 0.7852 0.6885
-2.250 0.0155 0.02963 0.02004 -0.0489 0.7607 0.7158
-2.000 0.0434 0.02959 0.01981 -0.0482 0.7491 0.7266
-1.750 0.0679 0.02953 0.01960 -0.0474 0.7373 0.7369
-1.500 0.0956 0.02938 0.01925 -0.0475 0.7275 0.7483
-1.250 0.1200 0.02932 0.01907 -0.0465 0.7168 0.7572
-1.000 0.1445 0.02921 0.01882 -0.0461 0.7072 0.7665
-0.750 0.1701 0.02911 0.01858 -0.0458 0.6982 0.7756
-0.500 0.1929 0.02905 0.01842 -0.0450 0.6890 0.7834
-0.250 0.2184 0.02896 0.01821 -0.0448 0.6810 0.7917
0.000 0.2409 0.02893 0.01810 -0.0441 0.6726 0.7988
0.250 0.2655 0.02887 0.01796 -0.0438 0.6647 0.8058
0.500 0.2892 0.02886 0.01786 -0.0435 0.6572 0.8125
0.750 0.3114 0.02887 0.01784 -0.0427 0.6494 0.8184
1.000 0.3400 0.02883 0.01767 -0.0433 0.6432 0.8246
1.250 0.3571 0.02896 0.01783 -0.0419 0.6347 0.8299
1.500 0.3843 0.02894 0.01774 -0.0420 0.6285 0.8351
1.750 0.4038 0.02915 0.01794 -0.0414 0.6209 0.8407
2.000 0.4269 0.02922 0.01800 -0.0409 0.6140 0.8450
2.250 0.4547 0.02925 0.01797 -0.0411 0.6082 0.8494
2.500 0.4710 0.02959 0.01836 -0.0400 0.6000 0.8544
2.750 0.4991 0.02965 0.01839 -0.0404 0.5941 0.8583
3.000 0.5175 0.02995 0.01873 -0.0394 0.5868 0.8625
3.250 0.5407 0.03017 0.01897 -0.0391 0.5797 0.8664
3.500 0.5707 0.03028 0.01905 -0.0398 0.5742 0.8701
3.750 0.5849 0.03081 0.01969 -0.0385 0.5656 0.8739
4.000 0.6141 0.03089 0.01975 -0.0389 0.5597 0.8771
4.250 0.6307 0.03142 0.02038 -0.0380 0.5518 0.8809
4.500 0.6563 0.03170 0.02071 -0.0381 0.5448 0.8843
4.750 0.6822 0.03203 0.02107 -0.0384 0.5381 0.8874
5.000 0.6992 0.03256 0.02171 -0.0374 0.5296 0.8906
5.250 0.7338 0.03250 0.02165 -0.0384 0.5241 0.8935
5.500 0.7426 0.03347 0.02279 -0.0368 0.5143 0.8975
5.750 0.7767 0.03347 0.02280 -0.0378 0.5081 0.9003
6.000 0.7871 0.03444 0.02394 -0.0365 0.4985 0.9036
6.250 0.8184 0.03446 0.02401 -0.0370 0.4918 0.9067
6.500 0.8292 0.03544 0.02516 -0.0357 0.4823 0.9110
6.750 0.8607 0.03548 0.02525 -0.0363 0.4751 0.9145
7.000 0.8702 0.03656 0.02652 -0.0349 0.4654 0.9188
7.250 0.9027 0.03649 0.02652 -0.0355 0.4581 0.9222
7.500 0.9090 0.03778 0.02800 -0.0340 0.4477 0.9271
7.750 0.9460 0.03746 0.02775 -0.0350 0.4407 0.9310
8.000 0.9456 0.03904 0.02955 -0.0329 0.4295 0.9381
8.250 0.9878 0.03839 0.02894 -0.0342 0.4228 0.9434
8.500 0.9835 0.04026 0.03105 -0.0322 0.4110 0.9552
8.750 0.9930 0.04137 0.03233 -0.0313 0.4011 0.9925
9.000 1.0264 0.04125 0.03230 -0.0322 0.3924 1.0000
9.250 1.0197 0.04380 0.03502 -0.0309 0.3809 1.0000
9.500 1.0491 0.04385 0.03516 -0.0314 0.3723 1.0000
9.750 1.0582 0.04538 0.03684 -0.0311 0.3619 1.0000
10.000 1.0507 0.04850 0.04009 -0.0307 0.3505 1.0000
10.250 1.0975 0.04686 0.03851 -0.0312 0.3428 1.0000
10.500 1.0852 0.05053 0.04233 -0.0311 0.3313 1.0000
10.750 1.0782 0.05412 0.04604 -0.0316 0.3203 1.0000
11.000 1.1352 0.05100 0.04296 -0.0313 0.3127 1.0000
11.250 1.1070 0.05692 0.04904 -0.0322 0.3010 1.0000
11.500 1.1045 0.06040 0.05263 -0.0330 0.2907 1.0000
11.750 1.1495 0.05810 0.05035 -0.0322 0.2825 1.0000
12.000 1.1169 0.06543 0.05784 -0.0342 0.2713 1.0000
12.250 1.1376 0.06603 0.05852 -0.0342 0.2627 1.0000
12.500 1.1427 0.06869 0.06126 -0.0349 0.2532 1.0000
12.750 1.1114 0.07676 0.06946 -0.0377 0.2431 1.0000
13.000 1.1691 0.07186 0.06455 -0.0354 0.2360 1.0000
13.250 1.1045 0.08522 0.07809 -0.0406 0.2254 1.0000
13.500 1.1618 0.07992 0.07280 -0.0378 0.2192 1.0000
13.750 1.0930 0.09484 0.08789 -0.0441 0.2090 1.0000
14.000 1.0648 0.10390 0.09702 -0.0481 0.1999 1.0000
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Polar data table (+)
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