NASA/LANGLEY NLF 0414F AIRFOIL (nlf414f-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: NASA/LANGLEY NLF 0414F AIRFOIL (nlf414f-il) Reynolds number: 1,000,000 Max Cl/Cd: 95.37 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-nlf414f-il-1000000-n5.txt Download as CSV file: xf-nlf414f-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.8320 0.04526 0.04203 -0.0641 0.7812 0.0066
-12.250 -0.8622 0.03936 0.03579 -0.0639 0.7808 0.0066
-12.000 -0.8746 0.03551 0.03167 -0.0633 0.7804 0.0067
-11.750 -0.8772 0.03258 0.02849 -0.0627 0.7800 0.0068
-11.500 -0.8742 0.03040 0.02608 -0.0617 0.7796 0.0068
-11.250 -0.8633 0.02851 0.02399 -0.0611 0.7791 0.0069
-11.000 -0.8489 0.02691 0.02219 -0.0607 0.7786 0.0070
-10.750 -0.8318 0.02553 0.02063 -0.0603 0.7781 0.0071
-10.500 -0.8128 0.02429 0.01925 -0.0601 0.7780 0.0071
-10.250 -0.7923 0.02320 0.01801 -0.0599 0.7778 0.0072
-10.000 -0.7706 0.02220 0.01688 -0.0598 0.7776 0.0072
-9.750 -0.7480 0.02130 0.01586 -0.0598 0.7775 0.0073
-9.500 -0.7247 0.02047 0.01493 -0.0597 0.7773 0.0073
-9.250 -0.7007 0.01971 0.01407 -0.0598 0.7771 0.0074
-9.000 -0.6779 0.01861 0.01285 -0.0597 0.7769 0.0074
-8.750 -0.6544 0.01765 0.01178 -0.0596 0.7767 0.0075
-8.500 -0.6298 0.01689 0.01095 -0.0597 0.7765 0.0077
-8.250 -0.6045 0.01626 0.01026 -0.0598 0.7763 0.0078
-8.000 -0.5787 0.01571 0.00965 -0.0599 0.7760 0.0079
-7.750 -0.5526 0.01521 0.00912 -0.0601 0.7758 0.0080
-7.500 -0.5261 0.01475 0.00862 -0.0603 0.7756 0.0081
-7.250 -0.4994 0.01432 0.00816 -0.0606 0.7753 0.0082
-7.000 -0.4726 0.01391 0.00772 -0.0608 0.7751 0.0083
-6.750 -0.4454 0.01354 0.00733 -0.0611 0.7748 0.0085
-6.500 -0.4181 0.01320 0.00697 -0.0614 0.7745 0.0087
-6.250 -0.3906 0.01287 0.00662 -0.0617 0.7741 0.0089
-6.000 -0.3630 0.01255 0.00628 -0.0620 0.7737 0.0092
-5.750 -0.3353 0.01224 0.00595 -0.0623 0.7734 0.0094
-5.500 -0.3074 0.01195 0.00564 -0.0627 0.7731 0.0096
-5.250 -0.2793 0.01169 0.00537 -0.0630 0.7727 0.0097
-5.000 -0.2513 0.01141 0.00507 -0.0634 0.7724 0.0100
-4.750 -0.2232 0.01114 0.00481 -0.0638 0.7721 0.0105
-4.500 -0.1947 0.01094 0.00460 -0.0642 0.7718 0.0110
-4.250 -0.1662 0.01075 0.00442 -0.0646 0.7714 0.0116
-4.000 -0.1375 0.01058 0.00425 -0.0650 0.7709 0.0122
-3.750 -0.1087 0.01041 0.00408 -0.0655 0.7704 0.0130
-3.500 -0.0800 0.01025 0.00394 -0.0659 0.7700 0.0145
-3.250 -0.0511 0.01011 0.00382 -0.0664 0.7697 0.0169
-3.000 -0.0222 0.00995 0.00370 -0.0669 0.7693 0.0222
-2.750 0.0067 0.00979 0.00359 -0.0673 0.7688 0.0320
-2.500 0.0356 0.00961 0.00349 -0.0678 0.7683 0.0465
-2.250 0.0645 0.00941 0.00339 -0.0683 0.7679 0.0725
-2.000 0.0931 0.00911 0.00328 -0.0689 0.7674 0.1263
-1.750 0.1211 0.00857 0.00313 -0.0696 0.7669 0.2409
-1.500 0.1484 0.00757 0.00288 -0.0706 0.7664 0.4643
-1.250 0.1753 0.00684 0.00299 -0.0711 0.7659 0.6907
-1.000 0.2054 0.00723 0.00335 -0.0714 0.7654 0.7329
-0.750 0.2347 0.00754 0.00369 -0.0715 0.7649 0.7424
-0.500 0.2646 0.00766 0.00377 -0.0720 0.7644 0.7464
-0.250 0.2941 0.00769 0.00380 -0.0725 0.7639 0.7477
0.000 0.3236 0.00775 0.00385 -0.0729 0.7633 0.7489
0.250 0.3530 0.00783 0.00394 -0.0733 0.7625 0.7504
0.500 0.3826 0.00787 0.00400 -0.0738 0.7617 0.7523
0.750 0.4124 0.00789 0.00404 -0.0743 0.7605 0.7540
1.000 0.4422 0.00787 0.00402 -0.0749 0.7587 0.7552
1.250 0.4721 0.00776 0.00392 -0.0754 0.7561 0.7558
1.500 0.5023 0.00754 0.00368 -0.0759 0.7527 0.7563
1.750 0.5325 0.00725 0.00334 -0.0763 0.7486 0.7569
2.000 0.5625 0.00713 0.00326 -0.0769 0.7426 0.7574
2.250 0.5926 0.00693 0.00306 -0.0774 0.7352 0.7577
2.500 0.6226 0.00682 0.00296 -0.0779 0.7227 0.7580
2.750 0.6495 0.00681 0.00260 -0.0777 0.6476 0.7583
3.000 0.6662 0.00828 0.00335 -0.0768 0.4960 0.7587
3.250 0.6863 0.00924 0.00388 -0.0763 0.4061 0.7591
3.500 0.7061 0.01008 0.00436 -0.0757 0.3276 0.7595
3.750 0.7256 0.01085 0.00480 -0.0751 0.2570 0.7597
4.000 0.7448 0.01156 0.00522 -0.0743 0.1957 0.7601
4.250 0.7657 0.01210 0.00557 -0.0738 0.1563 0.7606
4.500 0.7878 0.01254 0.00590 -0.0734 0.1309 0.7610
4.750 0.8099 0.01299 0.00625 -0.0730 0.1100 0.7613
5.000 0.8296 0.01343 0.00661 -0.0723 0.0943 0.7617
5.250 0.8503 0.01386 0.00697 -0.0716 0.0802 0.7619
5.500 0.8723 0.01431 0.00736 -0.0713 0.0676 0.7620
5.750 0.8942 0.01476 0.00774 -0.0709 0.0568 0.7622
6.250 0.9381 0.01561 0.00852 -0.0700 0.0436 0.7625
6.500 0.9598 0.01603 0.00892 -0.0695 0.0395 0.7627
6.750 0.9817 0.01643 0.00931 -0.0690 0.0367 0.7628
7.000 1.0028 0.01687 0.00973 -0.0685 0.0337 0.7630
7.250 1.0243 0.01728 0.01014 -0.0680 0.0320 0.7631
7.500 1.0453 0.01772 0.01058 -0.0674 0.0301 0.7633
7.750 1.0656 0.01820 0.01104 -0.0667 0.0281 0.7635
8.000 1.0863 0.01864 0.01150 -0.0661 0.0270 0.7637
8.250 1.1069 0.01909 0.01197 -0.0654 0.0261 0.7640
8.500 1.1269 0.01957 0.01246 -0.0647 0.0251 0.7641
8.750 1.1464 0.02008 0.01298 -0.0640 0.0241 0.7643
9.000 1.1654 0.02063 0.01354 -0.0632 0.0231 0.7644
9.250 1.1845 0.02117 0.01410 -0.0624 0.0224 0.7645
9.500 1.2040 0.02168 0.01463 -0.0616 0.0219 0.7646
9.750 1.2229 0.02222 0.01521 -0.0609 0.0212 0.7648
10.000 1.2413 0.02280 0.01581 -0.0600 0.0207 0.7649
10.250 1.2593 0.02340 0.01643 -0.0591 0.0201 0.7650
10.500 1.2770 0.02403 0.01708 -0.0582 0.0196 0.7652
10.750 1.2938 0.02471 0.01778 -0.0572 0.0190 0.7653
11.000 1.3095 0.02548 0.01858 -0.0561 0.0185 0.7654
11.250 1.3264 0.02615 0.01930 -0.0552 0.0183 0.7656
11.500 1.3428 0.02686 0.02005 -0.0542 0.0180 0.7657
11.750 1.3589 0.02758 0.02083 -0.0532 0.0177 0.7658
12.000 1.3749 0.02833 0.02161 -0.0522 0.0174 0.7660
12.250 1.3907 0.02909 0.02242 -0.0512 0.0170 0.7661
12.500 1.4056 0.02990 0.02327 -0.0502 0.0166 0.7662
12.750 1.4197 0.03077 0.02418 -0.0491 0.0163 0.7664
13.000 1.4335 0.03167 0.02512 -0.0480 0.0160 0.7665
13.250 1.4469 0.03262 0.02611 -0.0468 0.0157 0.7666
13.500 1.4589 0.03367 0.02722 -0.0456 0.0154 0.7668
13.750 1.4687 0.03492 0.02852 -0.0442 0.0151 0.7669
14.000 1.4796 0.03610 0.02977 -0.0430 0.0149 0.7670
14.250 1.4918 0.03720 0.03093 -0.0420 0.0148 0.7672
14.500 1.5028 0.03841 0.03222 -0.0409 0.0146 0.7673
14.750 1.5136 0.03967 0.03355 -0.0398 0.0145 0.7674
15.000 1.5238 0.04097 0.03493 -0.0387 0.0143 0.7676
15.250 1.5330 0.04241 0.03644 -0.0377 0.0141 0.7677
15.500 1.5419 0.04389 0.03799 -0.0367 0.0139 0.7678
15.750 1.5500 0.04547 0.03966 -0.0357 0.0138 0.7679
16.000 1.5577 0.04714 0.04140 -0.0347 0.0136 0.7681
16.250 1.5646 0.04889 0.04324 -0.0339 0.0135 0.7682
16.500 1.5710 0.05073 0.04516 -0.0330 0.0133 0.7683
16.750 1.5765 0.05272 0.04723 -0.0322 0.0132 0.7684
17.000 1.5814 0.05482 0.04941 -0.0316 0.0130 0.7686
17.250 1.5852 0.05709 0.05176 -0.0310 0.0129 0.7687
17.500 1.5881 0.05950 0.05426 -0.0305 0.0127 0.7688
17.750 1.5899 0.06209 0.05693 -0.0300 0.0126 0.7689
18.000 1.5906 0.06488 0.05981 -0.0298 0.0124 0.7690
18.250 1.5891 0.06802 0.06304 -0.0296 0.0123 0.7691
18.500 1.5854 0.07153 0.06666 -0.0297 0.0122 0.7693
18.750 1.5787 0.07554 0.07078 -0.0300 0.0120 0.7694
19.000 1.5701 0.07989 0.07524 -0.0305 0.0119 0.7695
19.250 1.5651 0.08389 0.07937 -0.0312 0.0119 0.7697
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Polar data table (+)
Polar graphs
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