NASA/LANGLEY NLF(1)-0416 AIRFOIL (nlf416-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY NLF(1)-0416 AIRFOIL (nlf416-il) Reynolds number: 1,000,000 Max Cl/Cd: 115.75 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nlf416-il-1000000.txt Download as CSV file: xf-nlf416-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.000 -0.7474 0.09418 0.09175 -0.0473 1.0000 0.0083
-15.750 -0.7758 0.08464 0.08204 -0.0529 1.0000 0.0083
-15.500 -0.8102 0.07464 0.07181 -0.0587 1.0000 0.0082
-15.250 -0.8031 0.07219 0.06939 -0.0601 1.0000 0.0085
-15.000 -0.8322 0.06395 0.06092 -0.0646 1.0000 0.0084
-14.750 -0.8522 0.05782 0.05459 -0.0675 1.0000 0.0083
-14.500 -0.8621 0.05353 0.05019 -0.0692 1.0000 0.0083
-14.250 -0.8621 0.05082 0.04743 -0.0702 1.0000 0.0085
-14.000 -0.8778 0.04651 0.04293 -0.0708 1.0000 0.0083
-13.750 -0.8792 0.04415 0.04049 -0.0710 1.0000 0.0085
-13.500 -0.8801 0.04197 0.03826 -0.0707 1.0000 0.0086
-13.250 -0.8839 0.03961 0.03579 -0.0701 1.0000 0.0087
-13.000 -0.8888 0.03723 0.03330 -0.0691 1.0000 0.0087
-12.750 -0.8909 0.03524 0.03121 -0.0679 1.0000 0.0087
-12.500 -0.8911 0.03358 0.02947 -0.0665 1.0000 0.0088
-12.250 -0.8933 0.03180 0.02759 -0.0646 1.0000 0.0088
-12.000 -0.8928 0.03048 0.02620 -0.0627 1.0000 0.0089
-11.750 -0.8938 0.02916 0.02480 -0.0603 1.0000 0.0090
-11.500 -0.8976 0.02786 0.02343 -0.0573 1.0000 0.0089
-11.250 -0.8944 0.02683 0.02233 -0.0554 0.9995 0.0091
-11.000 -0.8700 0.02545 0.02086 -0.0575 0.9969 0.0092
-10.750 -0.8425 0.02402 0.01933 -0.0599 0.9945 0.0093
-10.500 -0.8135 0.02281 0.01804 -0.0622 0.9921 0.0094
-10.250 -0.7855 0.02155 0.01671 -0.0642 0.9889 0.0095
-10.000 -0.7538 0.02042 0.01551 -0.0667 0.9864 0.0097
-9.750 -0.7194 0.01941 0.01443 -0.0695 0.9846 0.0098
-9.500 -0.6834 0.01855 0.01351 -0.0724 0.9832 0.0099
-9.250 -0.6633 0.01709 0.01198 -0.0726 0.9767 0.0102
-9.000 -0.6311 0.01598 0.01082 -0.0749 0.9735 0.0105
-8.750 -0.5955 0.01519 0.01000 -0.0774 0.9715 0.0108
-8.500 -0.5736 0.01459 0.00938 -0.0768 0.9628 0.0112
-8.250 -0.5393 0.01397 0.00874 -0.0787 0.9589 0.0117
-7.750 -0.4814 0.01285 0.00756 -0.0800 0.9373 0.0125
-7.500 -0.4324 0.01200 0.00664 -0.0851 0.9283 0.0132
-7.250 -0.3737 0.01136 0.00595 -0.0921 0.9118 0.0143
-7.000 -0.3298 0.01100 0.00543 -0.0957 0.8743 0.0152
-6.750 -0.3036 0.01080 0.00502 -0.0956 0.8304 0.0163
-6.500 -0.2805 0.01062 0.00470 -0.0948 0.7920 0.0181
-6.250 -0.2571 0.01044 0.00438 -0.0941 0.7581 0.0210
-6.000 -0.2333 0.01017 0.00404 -0.0937 0.7282 0.0304
-5.750 -0.2087 0.00974 0.00367 -0.0935 0.7016 0.0603
-5.250 -0.1564 0.00910 0.00315 -0.0937 0.6585 0.1242
-5.000 -0.1290 0.00882 0.00293 -0.0940 0.6407 0.1591
-4.750 -0.1011 0.00852 0.00273 -0.0944 0.6245 0.1993
-4.250 -0.0437 0.00793 0.00236 -0.0956 0.5965 0.2930
-4.000 -0.0143 0.00758 0.00218 -0.0963 0.5845 0.3550
-3.750 0.0156 0.00718 0.00199 -0.0972 0.5736 0.4302
-3.500 0.0458 0.00687 0.00184 -0.0980 0.5641 0.4954
-3.250 0.0754 0.00669 0.00179 -0.0986 0.5555 0.5476
-3.000 0.1048 0.00668 0.00183 -0.0988 0.5473 0.5856
-2.750 0.1338 0.00678 0.00190 -0.0989 0.5398 0.6051
-2.500 0.1632 0.00686 0.00193 -0.0991 0.5334 0.6173
-2.250 0.1920 0.00698 0.00201 -0.0992 0.5268 0.6254
-2.000 0.2214 0.00709 0.00203 -0.0994 0.5211 0.6323
-1.750 0.2503 0.00718 0.00211 -0.0995 0.5157 0.6373
-1.500 0.2791 0.00730 0.00219 -0.0995 0.5102 0.6423
-1.250 0.3082 0.00743 0.00225 -0.0997 0.5053 0.6470
-1.000 0.3374 0.00749 0.00229 -0.0998 0.5008 0.6508
-0.750 0.3660 0.00759 0.00238 -0.0998 0.4961 0.6541
-0.500 0.3944 0.00772 0.00246 -0.0998 0.4911 0.6573
-0.250 0.4235 0.00780 0.00253 -0.1000 0.4874 0.6604
0.000 0.4528 0.00789 0.00258 -0.1002 0.4833 0.6634
0.250 0.4817 0.00795 0.00261 -0.1003 0.4791 0.6660
0.500 0.5098 0.00805 0.00268 -0.1003 0.4744 0.6685
0.750 0.5385 0.00812 0.00276 -0.1004 0.4708 0.6706
1.000 0.5674 0.00818 0.00282 -0.1005 0.4670 0.6728
1.250 0.5961 0.00826 0.00289 -0.1006 0.4629 0.6751
1.500 0.6244 0.00837 0.00296 -0.1007 0.4584 0.6773
1.750 0.6532 0.00847 0.00304 -0.1008 0.4546 0.6794
2.000 0.6823 0.00854 0.00310 -0.1010 0.4509 0.6810
2.250 0.7110 0.00854 0.00311 -0.1012 0.4467 0.6830
2.500 0.7391 0.00861 0.00316 -0.1012 0.4423 0.6845
2.750 0.7673 0.00868 0.00324 -0.1013 0.4381 0.6858
3.000 0.7961 0.00872 0.00330 -0.1014 0.4341 0.6872
3.250 0.8244 0.00879 0.00337 -0.1015 0.4293 0.6885
3.500 0.8521 0.00891 0.00345 -0.1015 0.4239 0.6900
3.750 0.8808 0.00896 0.00353 -0.1016 0.4194 0.6916
4.000 0.9091 0.00903 0.00360 -0.1017 0.4140 0.6930
4.250 0.9369 0.00914 0.00369 -0.1017 0.4082 0.6944
4.500 0.9653 0.00921 0.00377 -0.1018 0.4028 0.6955
4.750 0.9934 0.00929 0.00385 -0.1019 0.3964 0.6964
5.000 1.0209 0.00941 0.00394 -0.1019 0.3895 0.6971
5.250 1.0490 0.00949 0.00403 -0.1020 0.3821 0.6976
5.500 1.0762 0.00960 0.00412 -0.1020 0.3736 0.6986
5.750 1.1037 0.00968 0.00420 -0.1020 0.3639 0.6998
6.000 1.1305 0.00982 0.00432 -0.1019 0.3533 0.7007
6.250 1.1568 0.01000 0.00447 -0.1017 0.3410 0.7015
6.500 1.1826 0.01022 0.00464 -0.1014 0.3278 0.7023
6.750 1.2084 0.01044 0.00483 -0.1011 0.3147 0.7031
7.000 1.2338 0.01068 0.00504 -0.1008 0.3011 0.7039
7.250 1.2588 0.01095 0.00527 -0.1004 0.2875 0.7047
7.500 1.2835 0.01124 0.00551 -0.1000 0.2743 0.7055
7.750 1.3077 0.01155 0.00578 -0.0995 0.2612 0.7065
8.000 1.3315 0.01188 0.00607 -0.0989 0.2481 0.7075
8.250 1.3549 0.01224 0.00638 -0.0983 0.2348 0.7086
8.500 1.3781 0.01259 0.00668 -0.0976 0.2219 0.7095
8.750 1.4012 0.01293 0.00699 -0.0970 0.2102 0.7103
9.000 1.4237 0.01329 0.00733 -0.0962 0.1989 0.7112
9.250 1.4453 0.01370 0.00770 -0.0953 0.1875 0.7120
9.750 1.4871 0.01455 0.00847 -0.0933 0.1656 0.7135
10.000 1.5065 0.01501 0.00890 -0.0921 0.1541 0.7141
10.250 1.5246 0.01551 0.00935 -0.0907 0.1426 0.7152
10.500 1.5408 0.01604 0.00984 -0.0890 0.1317 0.7164
10.750 1.5547 0.01653 0.01031 -0.0868 0.1226 0.7175
11.000 1.5688 0.01702 0.01080 -0.0847 0.1149 0.7186
11.250 1.5807 0.01764 0.01141 -0.0823 0.1069 0.7197
11.500 1.5939 0.01821 0.01198 -0.0801 0.1002 0.7208
11.750 1.6048 0.01889 0.01266 -0.0778 0.0935 0.7220
12.000 1.6157 0.01958 0.01336 -0.0755 0.0875 0.7233
12.250 1.6249 0.02038 0.01417 -0.0731 0.0818 0.7247
12.500 1.6332 0.02126 0.01505 -0.0707 0.0763 0.7260
12.750 1.6401 0.02225 0.01606 -0.0683 0.0713 0.7272
13.000 1.6466 0.02332 0.01715 -0.0661 0.0667 0.7284
13.250 1.6505 0.02462 0.01846 -0.0638 0.0623 0.7294
13.500 1.6566 0.02588 0.01976 -0.0620 0.0589 0.7304
13.750 1.6583 0.02753 0.02144 -0.0601 0.0551 0.7319
14.000 1.6621 0.02916 0.02314 -0.0586 0.0520 0.7335
14.250 1.6637 0.03110 0.02513 -0.0573 0.0488 0.7350
14.500 1.6625 0.03344 0.02751 -0.0561 0.0456 0.7365
14.750 1.6646 0.03563 0.02977 -0.0554 0.0430 0.7380
15.000 1.6622 0.03838 0.03258 -0.0548 0.0403 0.7395
15.250 1.6604 0.04123 0.03549 -0.0545 0.0378 0.7410
15.500 1.6588 0.04417 0.03849 -0.0544 0.0356 0.7425
15.750 1.6530 0.04770 0.04208 -0.0545 0.0333 0.7439
16.000 1.6500 0.05101 0.04546 -0.0547 0.0314 0.7453
16.250 1.6449 0.05465 0.04917 -0.0551 0.0294 0.7465
16.500 1.6366 0.05882 0.05340 -0.0558 0.0275 0.7482
16.750 1.6325 0.06257 0.05724 -0.0566 0.0259 0.7500
17.000 1.6254 0.06679 0.06155 -0.0575 0.0242 0.7517
17.250 1.6165 0.07140 0.06623 -0.0587 0.0225 0.7533
17.500 1.6110 0.07565 0.07057 -0.0599 0.0212 0.7552
17.750 1.6025 0.08042 0.07542 -0.0614 0.0199 0.7569
18.000 1.5930 0.08547 0.08055 -0.0631 0.0187 0.7587
18.250 1.5871 0.09009 0.08526 -0.0647 0.0177 0.7606
18.500 1.5791 0.09509 0.09034 -0.0666 0.0167 0.7623
18.750 1.5691 0.10052 0.09585 -0.0687 0.0159 0.7642
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