NASA/LANGLEY NLF(1)-0416 AIRFOIL (nlf416-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NASA/LANGLEY NLF(1)-0416 AIRFOIL (nlf416-il) Reynolds number: 500,000 Max Cl/Cd: 93.66 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-nlf416-il-500000.txt Download as CSV file: xf-nlf416-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.500 -0.4463 0.14553 0.14303 -0.0271 1.0000 0.0234
-14.250 -0.4381 0.14369 0.14120 -0.0271 1.0000 0.0237
-14.000 -0.5916 0.09305 0.09030 -0.0500 1.0000 0.0156
-13.750 -0.6197 0.08337 0.08052 -0.0558 1.0000 0.0154
-13.500 -0.6462 0.07481 0.07182 -0.0612 1.0000 0.0153
-13.250 -0.6708 0.06769 0.06456 -0.0654 1.0000 0.0152
-13.000 -0.6896 0.06224 0.05899 -0.0680 1.0000 0.0150
-12.750 -0.7099 0.05719 0.05380 -0.0699 1.0000 0.0148
-12.500 -0.7314 0.05257 0.04900 -0.0709 1.0000 0.0147
-12.250 -0.7508 0.04852 0.04478 -0.0708 1.0000 0.0144
-12.000 -0.7673 0.04522 0.04131 -0.0700 1.0000 0.0144
-11.750 -0.7825 0.04227 0.03818 -0.0684 1.0000 0.0144
-11.500 -0.7988 0.03942 0.03514 -0.0661 1.0000 0.0141
-11.250 -0.8108 0.03752 0.03310 -0.0633 1.0000 0.0142
-11.000 -0.8261 0.03588 0.03133 -0.0593 1.0000 0.0142
-10.750 -0.8399 0.03402 0.02931 -0.0554 1.0000 0.0141
-10.500 -0.8412 0.03235 0.02749 -0.0532 1.0000 0.0141
-10.250 -0.8392 0.03062 0.02560 -0.0508 1.0000 0.0141
-10.000 -0.8131 0.02859 0.02336 -0.0526 0.9977 0.0142
-9.750 -0.7809 0.02680 0.02139 -0.0551 0.9949 0.0144
-9.500 -0.7483 0.02527 0.01972 -0.0574 0.9920 0.0146
-9.250 -0.7159 0.02397 0.01827 -0.0593 0.9883 0.0150
-9.000 -0.6808 0.02292 0.01708 -0.0617 0.9854 0.0155
-8.750 -0.6436 0.02198 0.01604 -0.0644 0.9833 0.0157
-8.500 -0.6183 0.02031 0.01437 -0.0648 0.9776 0.0162
-8.250 -0.5842 0.01919 0.01326 -0.0670 0.9736 0.0167
-8.000 -0.5517 0.01825 0.01229 -0.0687 0.9685 0.0172
-7.750 -0.5199 0.01736 0.01137 -0.0703 0.9620 0.0179
-7.500 -0.4876 0.01651 0.01048 -0.0718 0.9557 0.0186
-7.250 -0.4566 0.01558 0.00951 -0.0731 0.9476 0.0194
-7.000 -0.4279 0.01465 0.00857 -0.0740 0.9371 0.0204
-6.750 -0.3906 0.01391 0.00781 -0.0764 0.9286 0.0219
-6.500 -0.3486 0.01308 0.00695 -0.0798 0.9173 0.0246
-6.250 -0.2970 0.01230 0.00616 -0.0852 0.9032 0.0304
-6.000 -0.2474 0.01116 0.00519 -0.0908 0.8798 0.0699
-5.750 -0.2101 0.01046 0.00464 -0.0935 0.8446 0.1259
-5.500 -0.1815 0.01005 0.00426 -0.0942 0.8079 0.1712
-5.250 -0.1555 0.00968 0.00394 -0.0943 0.7739 0.2221
-5.000 -0.1297 0.00933 0.00365 -0.0945 0.7434 0.2750
-4.750 -0.1032 0.00899 0.00339 -0.0947 0.7161 0.3303
-4.500 -0.0757 0.00859 0.00312 -0.0952 0.6929 0.3991
-4.250 -0.0475 0.00817 0.00291 -0.0958 0.6726 0.4805
-4.000 -0.0197 0.00799 0.00294 -0.0959 0.6550 0.5491
-3.750 0.0081 0.00815 0.00307 -0.0957 0.6396 0.5855
-3.500 0.0360 0.00837 0.00320 -0.0955 0.6257 0.6054
-3.250 0.0644 0.00857 0.00330 -0.0954 0.6131 0.6199
-3.000 0.0934 0.00878 0.00337 -0.0955 0.6023 0.6320
-2.750 0.1207 0.00905 0.00358 -0.0950 0.5929 0.6387
-2.500 0.1498 0.00924 0.00367 -0.0951 0.5840 0.6471
-2.250 0.1772 0.00946 0.00382 -0.0948 0.5759 0.6521
-2.000 0.2053 0.00965 0.00399 -0.0945 0.5685 0.6573
-1.750 0.2343 0.00984 0.00406 -0.0947 0.5616 0.6639
-1.500 0.2618 0.01001 0.00420 -0.0943 0.5554 0.6678
-1.250 0.2894 0.01017 0.00436 -0.0940 0.5491 0.6715
-1.000 0.3175 0.01035 0.00446 -0.0939 0.5434 0.6759
-0.750 0.3470 0.01049 0.00452 -0.0942 0.5380 0.6809
-0.500 0.3745 0.01056 0.00460 -0.0940 0.5327 0.6838
-0.250 0.4018 0.01071 0.00473 -0.0936 0.5275 0.6868
0.000 0.4296 0.01088 0.00485 -0.0935 0.5227 0.6901
0.250 0.4583 0.01095 0.00491 -0.0936 0.5179 0.6937
0.500 0.4879 0.01105 0.00495 -0.0940 0.5131 0.6976
0.750 0.5154 0.01113 0.00498 -0.0938 0.5085 0.6999
1.000 0.5429 0.01122 0.00509 -0.0936 0.5042 0.7022
1.250 0.5707 0.01129 0.00518 -0.0935 0.4995 0.7047
1.500 0.5987 0.01138 0.00525 -0.0935 0.4950 0.7074
1.750 0.6272 0.01153 0.00533 -0.0937 0.4904 0.7102
2.000 0.6565 0.01156 0.00536 -0.0940 0.4861 0.7129
2.250 0.6854 0.01158 0.00537 -0.0943 0.4814 0.7149
2.500 0.7130 0.01161 0.00540 -0.0942 0.4768 0.7165
2.750 0.7407 0.01173 0.00549 -0.0942 0.4722 0.7181
3.000 0.7686 0.01175 0.00556 -0.0942 0.4677 0.7197
3.250 0.7964 0.01179 0.00562 -0.0942 0.4630 0.7214
3.500 0.8242 0.01190 0.00569 -0.0942 0.4581 0.7232
3.750 0.8524 0.01197 0.00578 -0.0944 0.4533 0.7251
4.000 0.8807 0.01200 0.00584 -0.0945 0.4479 0.7269
4.250 0.9088 0.01208 0.00589 -0.0947 0.4425 0.7285
4.500 0.9371 0.01217 0.00597 -0.0949 0.4370 0.7299
4.750 0.9649 0.01217 0.00602 -0.0950 0.4309 0.7312
5.000 0.9919 0.01223 0.00606 -0.0949 0.4250 0.7322
5.250 1.0190 0.01228 0.00616 -0.0948 0.4188 0.7334
5.500 1.0459 0.01233 0.00625 -0.0947 0.4119 0.7346
5.750 1.0725 0.01244 0.00635 -0.0945 0.4051 0.7356
6.000 1.0996 0.01249 0.00645 -0.0945 0.3970 0.7366
6.250 1.1258 0.01261 0.00656 -0.0943 0.3891 0.7376
6.500 1.1524 0.01270 0.00668 -0.0941 0.3795 0.7389
6.750 1.1784 0.01283 0.00683 -0.0939 0.3698 0.7403
7.000 1.2036 0.01301 0.00698 -0.0936 0.3585 0.7413
7.250 1.2291 0.01318 0.00715 -0.0933 0.3461 0.7424
7.500 1.2541 0.01339 0.00735 -0.0929 0.3334 0.7434
7.750 1.2782 0.01366 0.00760 -0.0925 0.3199 0.7444
8.000 1.3016 0.01397 0.00787 -0.0919 0.3061 0.7453
8.250 1.3245 0.01432 0.00818 -0.0912 0.2923 0.7462
8.500 1.3465 0.01468 0.00852 -0.0904 0.2788 0.7473
8.750 1.3674 0.01507 0.00888 -0.0895 0.2652 0.7485
9.000 1.3881 0.01547 0.00926 -0.0885 0.2519 0.7497
9.250 1.4085 0.01588 0.00967 -0.0874 0.2389 0.7507
9.500 1.4280 0.01633 0.01011 -0.0862 0.2265 0.7518
9.750 1.4463 0.01681 0.01058 -0.0849 0.2148 0.7529
10.000 1.4620 0.01734 0.01108 -0.0831 0.2034 0.7541
10.250 1.4765 0.01785 0.01158 -0.0811 0.1926 0.7553
10.500 1.4913 0.01837 0.01212 -0.0792 0.1824 0.7566
10.750 1.5040 0.01901 0.01275 -0.0770 0.1725 0.7580
11.000 1.5152 0.01974 0.01345 -0.0748 0.1622 0.7593
11.250 1.5276 0.02042 0.01414 -0.0728 0.1522 0.7606
11.500 1.5373 0.02125 0.01495 -0.0705 0.1427 0.7619
11.750 1.5436 0.02226 0.01594 -0.0679 0.1334 0.7632
12.000 1.5534 0.02310 0.01683 -0.0659 0.1254 0.7648
12.250 1.5586 0.02425 0.01800 -0.0636 0.1184 0.7665
12.500 1.5651 0.02541 0.01920 -0.0616 0.1116 0.7681
12.750 1.5683 0.02685 0.02068 -0.0595 0.1056 0.7697
13.000 1.5729 0.02833 0.02220 -0.0578 0.0996 0.7714
13.250 1.5731 0.03025 0.02416 -0.0562 0.0942 0.7731
13.500 1.5770 0.03204 0.02602 -0.0550 0.0890 0.7749
13.750 1.5748 0.03450 0.02850 -0.0540 0.0841 0.7766
14.000 1.5774 0.03669 0.03077 -0.0533 0.0800 0.7782
14.250 1.5760 0.03936 0.03350 -0.0528 0.0757 0.7800
14.500 1.5722 0.04244 0.03665 -0.0525 0.0719 0.7818
14.750 1.5725 0.04517 0.03948 -0.0525 0.0684 0.7837
15.000 1.5678 0.04858 0.04295 -0.0526 0.0649 0.7856
15.250 1.5629 0.05213 0.04657 -0.0529 0.0617 0.7876
15.500 1.5608 0.05543 0.04997 -0.0533 0.0586 0.7897
15.750 1.5543 0.05938 0.05398 -0.0540 0.0556 0.7917
16.000 1.5479 0.06345 0.05812 -0.0548 0.0529 0.7937
16.250 1.5449 0.06713 0.06191 -0.0556 0.0502 0.7959
16.500 1.5378 0.07149 0.06634 -0.0568 0.0476 0.7980
16.750 1.5293 0.07616 0.07109 -0.0581 0.0453 0.8003
17.000 1.5262 0.08016 0.07520 -0.0593 0.0428 0.8032
17.250 1.5185 0.08495 0.08006 -0.0609 0.0405 0.8058
17.500 1.5083 0.09025 0.08542 -0.0628 0.0384 0.8084
17.750 1.5054 0.09448 0.08977 -0.0644 0.0361 0.8114
18.000 1.4968 0.09970 0.09507 -0.0665 0.0341 0.8141
18.250 1.4854 0.10550 0.10095 -0.0689 0.0323 0.8169
18.500 1.4810 0.11021 0.10579 -0.0710 0.0305 0.8207
18.750 1.4724 0.11571 0.11136 -0.0735 0.0288 0.8244
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