NASA/LANGLEY NLF 0414F AIRFOIL (nlf414f-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY NLF 0414F AIRFOIL (nlf414f-il) Reynolds number: 100,000 Max Cl/Cd: 34.4 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nlf414f-il-100000-n5.txt Download as CSV file: xf-nlf414f-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NASA/LANGLEY NLF 0414F 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3692 0.09964 0.09419 -0.0755 0.8857 0.0339
-10.750 -0.3640 0.09622 0.09078 -0.0770 0.8854 0.0332
-10.500 -0.3635 0.09138 0.08594 -0.0801 0.8851 0.0324
-10.000 -0.4253 0.06962 0.06380 -0.0979 0.8831 0.0284
-9.750 -0.4296 0.06613 0.06022 -0.0995 0.8821 0.0282
-9.500 -0.4365 0.06298 0.05695 -0.1004 0.8812 0.0280
-9.250 -0.4432 0.06011 0.05391 -0.1003 0.8803 0.0278
-9.000 -0.4465 0.05715 0.05075 -0.1000 0.8794 0.0276
-8.750 -0.4476 0.05430 0.04765 -0.0992 0.8781 0.0274
-8.500 -0.4467 0.05154 0.04460 -0.0980 0.8765 0.0272
-8.250 -0.4432 0.04890 0.04165 -0.0967 0.8752 0.0270
-8.000 -0.4373 0.04640 0.03881 -0.0952 0.8742 0.0269
-7.750 -0.4287 0.04406 0.03611 -0.0937 0.8731 0.0268
-7.500 -0.4168 0.04188 0.03356 -0.0922 0.8719 0.0268
-7.250 -0.4017 0.03986 0.03118 -0.0910 0.8707 0.0270
-7.000 -0.3840 0.03804 0.02900 -0.0899 0.8697 0.0272
-6.750 -0.3672 0.03652 0.02715 -0.0886 0.8687 0.0275
-6.500 -0.3517 0.03532 0.02563 -0.0869 0.8673 0.0282
-6.250 -0.3363 0.03438 0.02464 -0.0855 0.8654 0.0293
-6.000 -0.3193 0.03366 0.02386 -0.0842 0.8636 0.0306
-5.750 -0.3006 0.03285 0.02292 -0.0830 0.8624 0.0319
-5.500 -0.2804 0.03199 0.02193 -0.0818 0.8610 0.0328
-5.250 -0.2589 0.03118 0.02100 -0.0807 0.8595 0.0338
-5.000 -0.2375 0.03039 0.02020 -0.0798 0.8580 0.0350
-4.750 -0.2167 0.02978 0.01960 -0.0790 0.8568 0.0367
-4.500 -0.1953 0.02931 0.01909 -0.0782 0.8557 0.0395
-4.250 -0.1729 0.02884 0.01862 -0.0776 0.8547 0.0436
-4.000 -0.1664 0.02868 0.01844 -0.0745 0.8511 0.0471
-3.750 -0.1524 0.02836 0.01809 -0.0726 0.8487 0.0518
-3.500 -0.1341 0.02805 0.01779 -0.0714 0.8465 0.0620
-3.250 -0.1127 0.02761 0.01747 -0.0707 0.8444 0.0856
-3.000 -0.0943 0.02626 0.01719 -0.0701 0.8427 0.2756
-2.750 -0.0961 0.02619 0.01906 -0.0618 0.8409 0.6302
-2.500 -0.0709 0.02733 0.01999 -0.0612 0.8390 0.7419
-2.250 -0.0732 0.02816 0.02080 -0.0549 0.8338 0.7748
-2.000 -0.0730 0.02896 0.02165 -0.0470 0.8306 0.8079
-1.750 -0.0649 0.02939 0.02205 -0.0410 0.8280 0.8367
-1.500 -0.0405 0.02953 0.02204 -0.0401 0.8262 0.8474
-1.250 -0.0117 0.02962 0.02198 -0.0405 0.8248 0.8515
-1.000 -0.0101 0.02961 0.02193 -0.0364 0.8188 0.8572
-0.750 0.0120 0.02970 0.02191 -0.0360 0.8156 0.8622
-0.500 0.0381 0.02978 0.02187 -0.0361 0.8130 0.8660
-0.250 0.0669 0.02988 0.02188 -0.0365 0.8111 0.8691
0.000 0.0985 0.03003 0.02194 -0.0375 0.8095 0.8716
0.250 0.1056 0.03016 0.02204 -0.0350 0.8028 0.8754
0.500 0.1319 0.03032 0.02214 -0.0355 0.7993 0.8777
0.750 0.1622 0.03048 0.02224 -0.0365 0.7967 0.8795
1.000 0.1938 0.03060 0.02231 -0.0375 0.7947 0.8809
1.250 0.2078 0.03081 0.02252 -0.0359 0.7884 0.8831
1.500 0.2327 0.03097 0.02266 -0.0361 0.7839 0.8847
1.750 0.2632 0.03110 0.02277 -0.0369 0.7810 0.8861
2.000 0.2964 0.03122 0.02289 -0.0382 0.7789 0.8872
2.250 0.3101 0.03154 0.02322 -0.0369 0.7710 0.8887
2.500 0.3388 0.03169 0.02339 -0.0376 0.7670 0.8899
2.750 0.3718 0.03178 0.02351 -0.0388 0.7643 0.8910
3.000 0.3913 0.03207 0.02383 -0.0384 0.7571 0.8923
3.250 0.4195 0.03220 0.02402 -0.0391 0.7521 0.8930
3.500 0.4535 0.03221 0.02408 -0.0404 0.7492 0.8935
3.750 0.4717 0.03250 0.02444 -0.0398 0.7406 0.8948
4.000 0.5028 0.03241 0.02444 -0.0405 0.7363 0.8957
4.250 0.5239 0.03252 0.02462 -0.0400 0.7279 0.8968
4.500 0.5561 0.03226 0.02446 -0.0407 0.7225 0.8973
4.750 0.5796 0.03198 0.02428 -0.0402 0.7113 0.8980
5.000 0.6084 0.03105 0.02344 -0.0397 0.6975 0.8988
5.250 0.6377 0.03001 0.02250 -0.0392 0.6824 0.8998
5.500 0.6637 0.02941 0.02201 -0.0386 0.6678 0.9010
6.000 0.7117 0.02854 0.02138 -0.0372 0.6301 0.9027
6.250 0.7388 0.02779 0.02071 -0.0365 0.5988 0.9033
6.500 0.7926 0.02478 0.01746 -0.0368 0.5247 0.9036
6.750 0.8224 0.02391 0.01563 -0.0348 0.3833 0.9042
7.250 0.8395 0.02650 0.01704 -0.0307 0.2020 0.9068
7.500 0.8541 0.02759 0.01783 -0.0297 0.1574 0.9075
7.750 0.8703 0.02859 0.01866 -0.0288 0.1280 0.9083
8.000 0.8864 0.02961 0.01955 -0.0280 0.1080 0.9091
8.250 0.9027 0.03062 0.02051 -0.0272 0.0940 0.9099
8.500 0.9189 0.03157 0.02148 -0.0263 0.0839 0.9108
8.750 0.9339 0.03263 0.02253 -0.0253 0.0771 0.9118
9.000 0.9497 0.03362 0.02357 -0.0243 0.0713 0.9130
9.250 0.9641 0.03475 0.02470 -0.0233 0.0669 0.9145
9.500 0.9807 0.03574 0.02579 -0.0224 0.0627 0.9161
9.750 0.9967 0.03682 0.02692 -0.0215 0.0597 0.9177
10.000 1.0125 0.03807 0.02812 -0.0206 0.0574 0.9191
10.250 1.0322 0.03910 0.02934 -0.0200 0.0548 0.9205
10.500 1.0510 0.04020 0.03054 -0.0194 0.0522 0.9220
10.750 1.0687 0.04137 0.03175 -0.0188 0.0500 0.9237
11.000 1.0885 0.04266 0.03304 -0.0184 0.0484 0.9254
11.250 1.1107 0.04399 0.03453 -0.0179 0.0471 0.9275
11.500 1.1314 0.04543 0.03620 -0.0174 0.0456 0.9301
11.750 1.1492 0.04696 0.03794 -0.0168 0.0441 0.9335
12.000 1.1642 0.04851 0.03967 -0.0161 0.0427 0.9380
12.500 1.1908 0.05170 0.04306 -0.0144 0.0406 0.9738
12.750 1.2058 0.05401 0.04555 -0.0141 0.0399 1.0000
13.000 1.2120 0.05668 0.04859 -0.0130 0.0393 1.0000
13.250 1.2143 0.05963 0.05189 -0.0118 0.0388 1.0000
13.500 1.2119 0.06284 0.05545 -0.0105 0.0383 1.0000
13.750 1.2056 0.06630 0.05924 -0.0092 0.0378 1.0000
14.000 1.1961 0.07004 0.06328 -0.0081 0.0374 1.0000
14.250 1.1836 0.07409 0.06763 -0.0073 0.0370 1.0000
14.500 1.1683 0.07852 0.07234 -0.0069 0.0367 1.0000
14.750 1.1500 0.08348 0.07757 -0.0071 0.0364 1.0000
15.000 1.1280 0.08924 0.08360 -0.0080 0.0363 1.0000
15.250 1.1014 0.09622 0.09086 -0.0102 0.0363 1.0000
15.500 1.0672 0.10542 0.10036 -0.0145 0.0365 1.0000
15.750 1.0173 0.11967 0.11491 -0.0231 0.0371 1.0000
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Polar data table (+)
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