NASA/LANGLEY NLF(1)-0416 AIRFOIL (nlf416-il) Xfoil prediction polar at RE=50,000 Ncrit=9
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Airfoil: NASA/LANGLEY NLF(1)-0416 AIRFOIL (nlf416-il) Reynolds number: 50,000 Max Cl/Cd: 14.83 at α=0.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nlf416-il-50000.txt Download as CSV file: xf-nlf416-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4731 0.08982 0.08309 -0.0537 1.0000 0.1280
-9.750 -0.4365 0.08975 0.08303 -0.0486 1.0000 0.1312
-9.500 -0.5617 0.07613 0.06947 -0.0576 1.0000 0.1138
-9.250 -0.5774 0.07229 0.06562 -0.0566 1.0000 0.1124
-9.000 -0.5914 0.06846 0.06179 -0.0556 1.0000 0.1114
-8.750 -0.6058 0.06478 0.05805 -0.0543 1.0000 0.1102
-8.500 -0.6210 0.06109 0.05422 -0.0529 1.0000 0.1093
-8.250 -0.6327 0.05744 0.05037 -0.0514 1.0000 0.1086
-8.000 -0.6385 0.05392 0.04659 -0.0500 1.0000 0.1081
-7.750 -0.6393 0.05055 0.04292 -0.0486 1.0000 0.1081
-7.500 -0.6355 0.04734 0.03937 -0.0473 1.0000 0.1085
-7.250 -0.6275 0.04434 0.03600 -0.0462 1.0000 0.1092
-7.000 -0.6161 0.04166 0.03291 -0.0450 1.0000 0.1106
-6.750 -0.6028 0.03933 0.03014 -0.0438 1.0000 0.1137
-6.500 -0.5889 0.03759 0.02857 -0.0423 1.0000 0.1197
-6.250 -0.5738 0.03600 0.02668 -0.0410 1.0000 0.1266
-6.000 -0.5595 0.03455 0.02536 -0.0393 1.0000 0.1350
-5.750 -0.5458 0.03333 0.02417 -0.0376 1.0000 0.1476
-5.500 -0.5335 0.03228 0.02327 -0.0356 1.0000 0.1653
-5.250 -0.5220 0.03118 0.02239 -0.0337 1.0000 0.1941
-5.000 -0.5111 0.02970 0.02147 -0.0323 1.0000 0.2489
-4.750 -0.4990 0.02762 0.02059 -0.0318 1.0000 0.3737
-4.500 -0.4859 0.02874 0.02285 -0.0272 0.9937 0.5049
-4.250 -0.4564 0.03363 0.02780 -0.0213 0.9753 0.5732
-4.000 -0.4219 0.03774 0.03165 -0.0171 0.9594 0.6194
-3.750 -0.3891 0.04058 0.03426 -0.0134 0.9452 0.6557
-3.500 -0.3586 0.04221 0.03564 -0.0106 0.9317 0.6898
-3.250 -0.3310 0.04307 0.03628 -0.0082 0.9190 0.7217
-3.000 -0.3004 0.04348 0.03645 -0.0067 0.9072 0.7533
-2.750 -0.2501 0.04362 0.03630 -0.0085 0.8981 0.7873
-2.500 -0.2146 0.04336 0.03582 -0.0091 0.8870 0.8164
-2.250 -0.1582 0.04291 0.03508 -0.0136 0.8778 0.8461
-2.000 -0.0601 0.04202 0.03381 -0.0254 0.8698 0.8767
-1.750 0.0035 0.04126 0.03281 -0.0327 0.8608 0.9009
-1.500 0.1104 0.03973 0.03097 -0.0474 0.8534 0.9250
-1.250 0.1824 0.03864 0.02967 -0.0566 0.8456 0.9439
-1.000 0.2694 0.03721 0.02805 -0.0686 0.8369 0.9610
-0.750 0.3495 0.03586 0.02653 -0.0795 0.8290 0.9761
-0.500 0.4126 0.03493 0.02550 -0.0876 0.8193 0.9886
-0.250 0.4670 0.03432 0.02481 -0.0943 0.8097 0.9991
0.000 0.4946 0.03431 0.02473 -0.0957 0.8006 1.0000
0.250 0.4887 0.03550 0.02592 -0.0919 0.7894 1.0000
0.500 0.5229 0.03527 0.02563 -0.0939 0.7820 1.0000
0.750 0.4980 0.03722 0.02761 -0.0875 0.7706 1.0000
1.000 0.5400 0.03678 0.02710 -0.0903 0.7640 1.0000
1.250 0.4933 0.03949 0.02987 -0.0811 0.7525 1.0000
1.500 0.5188 0.03973 0.03007 -0.0815 0.7454 1.0000
1.750 0.4636 0.04247 0.03287 -0.0714 0.7352 1.0000
2.000 0.5017 0.04249 0.03285 -0.0735 0.7286 1.0000
2.250 0.4090 0.04595 0.03636 -0.0590 0.7196 1.0000
2.500 0.4686 0.04549 0.03587 -0.0634 0.7127 1.0000
2.750 0.3782 0.04868 0.03909 -0.0501 0.7058 1.0000
3.000 0.3803 0.04959 0.04000 -0.0478 0.6987 1.0000
3.250 0.3695 0.05082 0.04122 -0.0440 0.6922 1.0000
3.500 0.3366 0.05233 0.04274 -0.0380 0.6870 1.0000
3.750 0.3671 0.05284 0.04323 -0.0386 0.6788 1.0000
4.000 0.3303 0.05443 0.04483 -0.0327 0.6745 1.0000
4.250 0.3169 0.05589 0.04629 -0.0299 0.6694 1.0000
4.500 0.3506 0.05684 0.04724 -0.0312 0.6596 1.0000
4.750 0.3394 0.05891 0.04934 -0.0301 0.6547 1.0000
5.000 0.3829 0.05991 0.05034 -0.0323 0.6432 1.0000
5.250 0.3716 0.06242 0.05289 -0.0320 0.6385 1.0000
5.500 0.3890 0.06435 0.05485 -0.0333 0.6308 1.0000
5.750 0.4054 0.06639 0.05692 -0.0345 0.6217 1.0000
6.000 0.4127 0.06893 0.05952 -0.0358 0.6172 1.0000
6.250 0.3917 0.07486 0.06556 -0.0396 0.6590 1.0000
6.500 0.4192 0.07684 0.06758 -0.0412 0.6424 1.0000
6.750 0.4651 0.07615 0.06690 -0.0407 0.5954 1.0000
7.000 0.4763 0.07937 0.07019 -0.0428 0.5945 1.0000
7.250 0.4942 0.08261 0.07350 -0.0450 0.5913 1.0000
7.500 0.5179 0.08451 0.07545 -0.0460 0.5742 1.0000
8.000 0.5716 0.08826 0.07934 -0.0481 0.5408 1.0000
9.000 0.5407 0.10596 0.09737 -0.0572 0.5782 1.0000
9.250 0.5464 0.10874 0.10021 -0.0582 0.5669 1.0000
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Polar data table (+)
Polar graphs
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