NASA/LANGLEY NLF(1)-0416 AIRFOIL (nlf416-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY NLF(1)-0416 AIRFOIL (nlf416-il) Reynolds number: 200,000 Max Cl/Cd: 67.31 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nlf416-il-200000-n5.txt Download as CSV file: xf-nlf416-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.500 -0.6166 0.08068 0.07631 -0.0577 1.0000 0.0141
-13.250 -0.6494 0.07125 0.06664 -0.0637 1.0000 0.0140
-13.000 -0.6735 0.06460 0.05978 -0.0673 1.0000 0.0139
-12.750 -0.6928 0.05939 0.05437 -0.0695 1.0000 0.0139
-12.500 -0.7097 0.05498 0.04977 -0.0706 1.0000 0.0139
-12.250 -0.7224 0.05143 0.04604 -0.0709 1.0000 0.0139
-12.000 -0.7333 0.04829 0.04272 -0.0705 1.0000 0.0139
-11.750 -0.7417 0.04559 0.03987 -0.0696 1.0000 0.0140
-11.500 -0.7485 0.04319 0.03731 -0.0682 1.0000 0.0140
-11.250 -0.7540 0.04107 0.03504 -0.0665 1.0000 0.0141
-11.000 -0.7584 0.03921 0.03303 -0.0644 1.0000 0.0142
-10.750 -0.7626 0.03754 0.03123 -0.0619 1.0000 0.0143
-10.500 -0.7674 0.03609 0.02967 -0.0589 1.0000 0.0144
-10.250 -0.7731 0.03482 0.02829 -0.0555 1.0000 0.0145
-10.000 -0.7724 0.03341 0.02676 -0.0530 1.0000 0.0147
-9.750 -0.7678 0.03204 0.02528 -0.0509 1.0000 0.0149
-9.500 -0.7374 0.03035 0.02341 -0.0532 0.9959 0.0152
-9.250 -0.7072 0.02883 0.02169 -0.0552 0.9915 0.0157
-9.000 -0.6779 0.02738 0.02023 -0.0572 0.9861 0.0161
-8.750 -0.6482 0.02613 0.01893 -0.0591 0.9804 0.0165
-8.500 -0.6195 0.02496 0.01772 -0.0607 0.9733 0.0171
-8.250 -0.5933 0.02392 0.01660 -0.0616 0.9644 0.0181
-8.000 -0.5654 0.02295 0.01552 -0.0626 0.9552 0.0190
-7.500 -0.5114 0.02091 0.01345 -0.0645 0.9328 0.0213
-7.250 -0.4825 0.01997 0.01242 -0.0656 0.9210 0.0226
-7.000 -0.4497 0.01899 0.01139 -0.0675 0.9096 0.0241
-6.750 -0.4112 0.01810 0.01042 -0.0703 0.8979 0.0269
-6.500 -0.3685 0.01720 0.00947 -0.0740 0.8834 0.0321
-6.250 -0.3245 0.01627 0.00856 -0.0781 0.8651 0.0438
-6.000 -0.2817 0.01538 0.00773 -0.0819 0.8422 0.0702
-5.750 -0.2422 0.01459 0.00705 -0.0851 0.8169 0.1118
-5.500 -0.2098 0.01387 0.00649 -0.0870 0.7897 0.1645
-5.250 -0.1805 0.01323 0.00600 -0.0882 0.7634 0.2265
-5.000 -0.1529 0.01264 0.00558 -0.0890 0.7387 0.2916
-4.750 -0.1256 0.01214 0.00523 -0.0896 0.7167 0.3586
-4.500 -0.0982 0.01178 0.00499 -0.0899 0.6978 0.4165
-4.250 -0.0713 0.01159 0.00489 -0.0899 0.6810 0.4670
-4.000 -0.0451 0.01159 0.00500 -0.0893 0.6658 0.5133
-3.750 -0.0198 0.01186 0.00534 -0.0883 0.6518 0.5505
-3.500 0.0066 0.01218 0.00560 -0.0874 0.6390 0.5767
-3.250 0.0345 0.01240 0.00568 -0.0872 0.6271 0.5968
-3.000 0.0629 0.01259 0.00573 -0.0871 0.6162 0.6116
-2.750 0.0910 0.01280 0.00580 -0.0870 0.6071 0.6228
-2.500 0.1200 0.01295 0.00581 -0.0872 0.5979 0.6339
-2.250 0.1470 0.01322 0.00598 -0.0866 0.5899 0.6409
-2.000 0.1762 0.01334 0.00596 -0.0869 0.5815 0.6496
-1.750 0.2026 0.01359 0.00613 -0.0863 0.5748 0.6542
-1.500 0.2310 0.01372 0.00618 -0.0863 0.5679 0.6609
-1.250 0.2593 0.01385 0.00621 -0.0863 0.5613 0.6667
-1.000 0.2859 0.01404 0.00635 -0.0858 0.5554 0.6705
-0.750 0.3137 0.01416 0.00642 -0.0857 0.5492 0.6754
-0.500 0.3439 0.01423 0.00635 -0.0864 0.5436 0.6816
-0.250 0.3702 0.01438 0.00647 -0.0858 0.5385 0.6842
0.000 0.3971 0.01449 0.00658 -0.0854 0.5328 0.6874
0.250 0.4249 0.01461 0.00664 -0.0854 0.5277 0.6912
0.500 0.4543 0.01470 0.00663 -0.0859 0.5229 0.6959
0.750 0.4828 0.01474 0.00667 -0.0860 0.5176 0.6991
1.000 0.5096 0.01484 0.00676 -0.0857 0.5125 0.7013
1.250 0.5369 0.01496 0.00683 -0.0856 0.5080 0.7037
1.500 0.5648 0.01504 0.00690 -0.0856 0.5030 0.7063
1.750 0.5933 0.01510 0.00696 -0.0858 0.4978 0.7091
2.000 0.6225 0.01518 0.00698 -0.0863 0.4930 0.7121
2.250 0.6517 0.01526 0.00701 -0.0867 0.4885 0.7147
2.500 0.6786 0.01533 0.00713 -0.0865 0.4830 0.7163
2.750 0.7056 0.01542 0.00723 -0.0864 0.4780 0.7180
3.000 0.7330 0.01554 0.00731 -0.0863 0.4734 0.7198
3.250 0.7605 0.01561 0.00745 -0.0863 0.4679 0.7218
3.500 0.7882 0.01569 0.00755 -0.0864 0.4622 0.7237
3.750 0.8161 0.01581 0.00762 -0.0866 0.4572 0.7258
4.000 0.8443 0.01589 0.00776 -0.0868 0.4515 0.7278
4.250 0.8726 0.01598 0.00786 -0.0871 0.4454 0.7296
4.500 0.8999 0.01611 0.00795 -0.0872 0.4401 0.7312
4.750 0.9264 0.01619 0.00814 -0.0870 0.4336 0.7323
5.000 0.9527 0.01629 0.00828 -0.0868 0.4271 0.7334
5.250 0.9791 0.01642 0.00842 -0.0866 0.4207 0.7345
5.500 1.0051 0.01652 0.00861 -0.0864 0.4130 0.7359
5.750 1.0308 0.01667 0.00876 -0.0861 0.4060 0.7374
6.000 1.0569 0.01679 0.00897 -0.0859 0.3975 0.7389
6.250 1.0824 0.01694 0.00913 -0.0857 0.3895 0.7402
6.500 1.1081 0.01709 0.00935 -0.0855 0.3801 0.7415
6.750 1.1332 0.01727 0.00956 -0.0852 0.3707 0.7428
7.000 1.1577 0.01747 0.00978 -0.0848 0.3604 0.7441
7.250 1.1822 0.01769 0.01004 -0.0844 0.3489 0.7457
7.500 1.2054 0.01794 0.01032 -0.0838 0.3373 0.7472
7.750 1.2270 0.01823 0.01062 -0.0829 0.3252 0.7483
8.250 1.2681 0.01895 0.01136 -0.0808 0.2993 0.7506
8.500 1.2879 0.01936 0.01179 -0.0797 0.2867 0.7519
8.750 1.3067 0.01982 0.01227 -0.0785 0.2742 0.7532
9.000 1.3243 0.02033 0.01279 -0.0771 0.2622 0.7546
9.250 1.3402 0.02089 0.01335 -0.0755 0.2503 0.7560
9.500 1.3554 0.02143 0.01391 -0.0737 0.2385 0.7575
9.750 1.3689 0.02201 0.01453 -0.0717 0.2278 0.7591
10.000 1.3809 0.02271 0.01524 -0.0696 0.2175 0.7608
10.500 1.4037 0.02422 0.01682 -0.0656 0.1974 0.7643
10.750 1.4119 0.02514 0.01777 -0.0633 0.1885 0.7659
11.000 1.4208 0.02608 0.01878 -0.0612 0.1792 0.7674
11.250 1.4281 0.02715 0.01990 -0.0591 0.1709 0.7691
11.500 1.4334 0.02840 0.02120 -0.0571 0.1628 0.7709
11.750 1.4399 0.02969 0.02256 -0.0554 0.1551 0.7728
12.000 1.4425 0.03132 0.02422 -0.0537 0.1480 0.7747
12.250 1.4478 0.03290 0.02589 -0.0525 0.1410 0.7767
12.500 1.4486 0.03494 0.02798 -0.0513 0.1344 0.7786
12.750 1.4519 0.03688 0.03003 -0.0503 0.1281 0.7803
13.000 1.4516 0.03926 0.03247 -0.0496 0.1221 0.7821
13.250 1.4524 0.04169 0.03499 -0.0491 0.1164 0.7841
13.500 1.4520 0.04437 0.03775 -0.0489 0.1106 0.7862
13.750 1.4498 0.04736 0.04080 -0.0489 0.1057 0.7885
14.000 1.4498 0.05022 0.04377 -0.0490 0.1001 0.7909
14.250 1.4449 0.05375 0.04733 -0.0494 0.0954 0.7934
14.500 1.4444 0.05680 0.05050 -0.0497 0.0904 0.7958
14.750 1.4403 0.06038 0.05416 -0.0503 0.0858 0.7980
15.000 1.4360 0.06407 0.05793 -0.0510 0.0819 0.8004
15.250 1.4339 0.06760 0.06157 -0.0518 0.0775 0.8030
15.500 1.4281 0.07174 0.06577 -0.0529 0.0738 0.8055
15.750 1.4250 0.07560 0.06974 -0.0539 0.0703 0.8082
16.000 1.4218 0.07958 0.07382 -0.0551 0.0667 0.8109
16.250 1.4153 0.08408 0.07840 -0.0566 0.0637 0.8135
16.500 1.4117 0.08825 0.08268 -0.0580 0.0608 0.8166
16.750 1.4083 0.09247 0.08702 -0.0595 0.0578 0.8200
17.000 1.4018 0.09729 0.09193 -0.0614 0.0551 0.8235
17.250 1.3960 0.10206 0.09679 -0.0633 0.0527 0.8272
17.500 1.3926 0.10647 0.10135 -0.0651 0.0501 0.8315
17.750 1.3866 0.11138 0.10637 -0.0672 0.0477 0.8364
18.000 1.3783 0.11678 0.11184 -0.0698 0.0458 0.8415
18.250 1.3747 0.12132 0.11655 -0.0718 0.0436 0.8484
18.750 1.3612 0.13152 0.12699 -0.0767 0.0397 0.8693
19.000 1.3519 0.13631 0.13192 -0.0786 0.0382 0.9062
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Polar data table (+)
Polar graphs
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