NACA 2414 (n2414-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 2414 (n2414-il) Reynolds number: 100,000 Max Cl/Cd: 48.11 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-n2414-il-100000-n5.txt Download as CSV file: xf-n2414-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 2414
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.7162 0.08156 0.07545 -0.0513 1.0000 0.0501
-13.000 -0.7866 0.06543 0.05900 -0.0639 1.0000 0.0493
-12.750 -0.8221 0.05769 0.05097 -0.0690 1.0000 0.0492
-12.500 -0.8474 0.05262 0.04563 -0.0708 1.0000 0.0495
-12.250 -0.8683 0.04892 0.04166 -0.0701 1.0000 0.0500
-12.000 -0.8872 0.04610 0.03855 -0.0673 1.0000 0.0505
-11.750 -0.8932 0.04407 0.03638 -0.0646 1.0000 0.0512
-11.500 -0.8885 0.04270 0.03499 -0.0625 1.0000 0.0520
-11.250 -0.8851 0.04125 0.03347 -0.0602 1.0000 0.0530
-11.000 -0.8816 0.03975 0.03184 -0.0577 1.0000 0.0540
-10.750 -0.8778 0.03818 0.03009 -0.0551 1.0000 0.0554
-10.500 -0.8739 0.03650 0.02811 -0.0524 1.0000 0.0571
-10.250 -0.8654 0.03518 0.02668 -0.0501 1.0000 0.0585
-10.000 -0.8542 0.03422 0.02573 -0.0480 1.0000 0.0600
-9.750 -0.8434 0.03315 0.02457 -0.0458 1.0000 0.0617
-9.500 -0.8324 0.03199 0.02321 -0.0435 1.0000 0.0639
-9.250 -0.8205 0.03084 0.02189 -0.0414 1.0000 0.0661
-9.000 -0.8070 0.03003 0.02111 -0.0394 1.0000 0.0680
-8.750 -0.7932 0.02917 0.02019 -0.0375 1.0000 0.0705
-8.500 -0.7787 0.02826 0.01909 -0.0355 1.0000 0.0735
-8.250 -0.7639 0.02744 0.01826 -0.0337 1.0000 0.0761
-8.000 -0.7484 0.02675 0.01755 -0.0320 1.0000 0.0792
-7.750 -0.7320 0.02602 0.01668 -0.0303 1.0000 0.0829
-7.500 -0.7158 0.02532 0.01598 -0.0287 1.0000 0.0863
-7.250 -0.6961 0.02472 0.01535 -0.0277 0.9993 0.0907
-7.000 -0.6621 0.02397 0.01453 -0.0295 0.9949 0.0967
-6.750 -0.6285 0.02335 0.01387 -0.0312 0.9901 0.1037
-6.500 -0.5945 0.02271 0.01322 -0.0330 0.9850 0.1111
-6.250 -0.5600 0.02216 0.01260 -0.0347 0.9800 0.1203
-6.000 -0.5268 0.02161 0.01208 -0.0362 0.9739 0.1301
-5.750 -0.4901 0.02108 0.01158 -0.0384 0.9693 0.1417
-5.500 -0.4594 0.02060 0.01111 -0.0393 0.9617 0.1539
-5.250 -0.4224 0.02013 0.01067 -0.0414 0.9566 0.1689
-5.000 -0.3913 0.01970 0.01028 -0.0423 0.9488 0.1845
-4.750 -0.3553 0.01928 0.00990 -0.0441 0.9428 0.2032
-4.500 -0.3218 0.01889 0.00956 -0.0454 0.9360 0.2233
-4.250 -0.2886 0.01852 0.00922 -0.0466 0.9286 0.2454
-4.000 -0.2511 0.01809 0.00890 -0.0486 0.9238 0.2702
-3.750 -0.2243 0.01778 0.00866 -0.0484 0.9135 0.2938
-3.500 -0.1886 0.01739 0.00836 -0.0499 0.9078 0.3220
-3.250 -0.1617 0.01709 0.00815 -0.0496 0.8974 0.3497
-3.000 -0.1277 0.01669 0.00787 -0.0507 0.8909 0.3823
-2.750 -0.1012 0.01639 0.00770 -0.0503 0.8801 0.4149
-2.500 -0.0682 0.01601 0.00747 -0.0510 0.8731 0.4551
-2.250 -0.0426 0.01574 0.00736 -0.0503 0.8614 0.4963
-2.000 -0.0124 0.01542 0.00721 -0.0503 0.8526 0.5421
-1.750 0.0149 0.01518 0.00711 -0.0497 0.8416 0.5879
-1.500 0.0424 0.01495 0.00703 -0.0491 0.8305 0.6334
-1.250 0.0726 0.01472 0.00692 -0.0488 0.8209 0.6795
-1.000 0.0990 0.01460 0.00691 -0.0479 0.8080 0.7218
-0.750 0.1274 0.01449 0.00688 -0.0471 0.7964 0.7627
-0.500 0.1582 0.01439 0.00682 -0.0468 0.7853 0.8016
-0.250 0.1879 0.01439 0.00685 -0.0464 0.7715 0.8367
0.000 0.2206 0.01441 0.00685 -0.0466 0.7584 0.8685
0.250 0.2572 0.01443 0.00683 -0.0476 0.7453 0.8956
0.500 0.2936 0.01446 0.00678 -0.0487 0.7320 0.9204
0.750 0.3328 0.01453 0.00678 -0.0506 0.7169 0.9403
1.000 0.3733 0.01459 0.00677 -0.0529 0.7017 0.9579
1.250 0.4164 0.01465 0.00674 -0.0558 0.6864 0.9726
1.500 0.4606 0.01470 0.00671 -0.0591 0.6707 0.9860
1.750 0.5063 0.01474 0.00667 -0.0627 0.6548 0.9985
2.000 0.5309 0.01481 0.00664 -0.0622 0.6405 1.0000
2.250 0.5526 0.01491 0.00665 -0.0610 0.6264 1.0000
2.500 0.5739 0.01504 0.00672 -0.0598 0.6118 1.0000
2.750 0.5955 0.01518 0.00680 -0.0586 0.5976 1.0000
3.000 0.6173 0.01534 0.00689 -0.0574 0.5840 1.0000
3.250 0.6395 0.01552 0.00699 -0.0563 0.5707 1.0000
3.500 0.6613 0.01571 0.00713 -0.0551 0.5568 1.0000
3.750 0.6830 0.01591 0.00730 -0.0538 0.5428 1.0000
4.000 0.7047 0.01613 0.00748 -0.0526 0.5290 1.0000
4.250 0.7266 0.01636 0.00766 -0.0514 0.5151 1.0000
4.500 0.7484 0.01660 0.00784 -0.0501 0.5011 1.0000
4.750 0.7698 0.01686 0.00807 -0.0489 0.4863 1.0000
5.000 0.7912 0.01712 0.00832 -0.0476 0.4709 1.0000
5.250 0.8126 0.01740 0.00858 -0.0463 0.4554 1.0000
5.500 0.8338 0.01769 0.00886 -0.0450 0.4395 1.0000
5.750 0.8547 0.01800 0.00914 -0.0437 0.4230 1.0000
6.000 0.8754 0.01832 0.00944 -0.0424 0.4057 1.0000
6.250 0.8957 0.01866 0.00976 -0.0410 0.3877 1.0000
6.500 0.9155 0.01903 0.01010 -0.0396 0.3690 1.0000
6.750 0.9347 0.01944 0.01046 -0.0381 0.3498 1.0000
7.000 0.9534 0.01989 0.01086 -0.0365 0.3302 1.0000
7.250 0.9718 0.02037 0.01132 -0.0350 0.3097 1.0000
7.500 0.9894 0.02090 0.01180 -0.0334 0.2890 1.0000
7.750 1.0060 0.02150 0.01233 -0.0316 0.2686 1.0000
8.000 1.0214 0.02216 0.01292 -0.0298 0.2489 1.0000
8.250 1.0370 0.02284 0.01356 -0.0280 0.2296 1.0000
8.500 1.0514 0.02358 0.01425 -0.0261 0.2112 1.0000
8.750 1.0648 0.02437 0.01500 -0.0241 0.1942 1.0000
9.000 1.0770 0.02521 0.01581 -0.0220 0.1787 1.0000
9.250 1.0871 0.02608 0.01666 -0.0196 0.1650 1.0000
9.500 1.0964 0.02704 0.01758 -0.0172 0.1528 1.0000
10.000 1.1145 0.02915 0.01969 -0.0128 0.1319 1.0000
10.250 1.1231 0.03031 0.02087 -0.0107 0.1234 1.0000
10.500 1.1297 0.03163 0.02216 -0.0087 0.1161 1.0000
10.750 1.1386 0.03289 0.02349 -0.0070 0.1089 1.0000
11.000 1.1437 0.03442 0.02500 -0.0052 0.1035 1.0000
11.250 1.1520 0.03583 0.02652 -0.0037 0.0977 1.0000
11.500 1.1570 0.03749 0.02820 -0.0023 0.0931 1.0000
11.750 1.1630 0.03918 0.02995 -0.0009 0.0889 1.0000
12.000 1.1688 0.04093 0.03179 0.0002 0.0848 1.0000
12.250 1.1719 0.04293 0.03379 0.0013 0.0816 1.0000
12.500 1.1778 0.04483 0.03583 0.0022 0.0781 1.0000
12.750 1.1823 0.04688 0.03796 0.0029 0.0750 1.0000
13.000 1.1851 0.04910 0.04021 0.0036 0.0726 1.0000
13.250 1.1890 0.05134 0.04253 0.0042 0.0701 1.0000
13.500 1.1925 0.05367 0.04501 0.0046 0.0675 1.0000
13.750 1.1948 0.05613 0.04754 0.0049 0.0653 1.0000
14.000 1.1969 0.05862 0.05005 0.0051 0.0635 1.0000
14.250 1.1988 0.06128 0.05286 0.0052 0.0617 1.0000
14.500 1.1995 0.06415 0.05590 0.0052 0.0598 1.0000
14.750 1.1996 0.06711 0.05897 0.0049 0.0580 1.0000
15.000 1.2000 0.07004 0.06195 0.0046 0.0566 1.0000
15.250 1.2022 0.07272 0.06461 0.0045 0.0553 1.0000
15.500 1.1979 0.07659 0.06874 0.0036 0.0540 1.0000
15.750 1.1931 0.08059 0.07295 0.0026 0.0527 1.0000
16.000 1.1880 0.08467 0.07719 0.0014 0.0515 1.0000
16.250 1.1836 0.08871 0.08135 0.0001 0.0505 1.0000
16.500 1.1811 0.09245 0.08516 -0.0011 0.0495 1.0000
16.750 1.1834 0.09538 0.08808 -0.0018 0.0486 1.0000
17.000 1.1690 0.10147 0.09443 -0.0046 0.0479 1.0000
17.250 1.1515 0.10834 0.10156 -0.0080 0.0473 1.0000
17.500 1.1305 0.11619 0.10967 -0.0122 0.0467 1.0000
17.750 1.1028 0.12586 0.11961 -0.0178 0.0464 1.0000
18.000 1.0395 0.14467 0.13878 -0.0297 0.0465 1.0000
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