NACA 2414 (n2414-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 2414 (n2414-il) Reynolds number: 500,000 Max Cl/Cd: 87.57 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n2414-il-500000.txt Download as CSV file: xf-n2414-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -0.9646 0.10148 0.09806 -0.0372 1.0000 0.0265
-17.500 -0.9974 0.09157 0.08796 -0.0433 1.0000 0.0265
-17.250 -1.0183 0.08419 0.08045 -0.0478 1.0000 0.0266
-17.000 -1.0353 0.07772 0.07386 -0.0517 1.0000 0.0267
-16.750 -1.0497 0.07185 0.06787 -0.0553 1.0000 0.0269
-16.500 -1.0622 0.06632 0.06223 -0.0587 1.0000 0.0270
-16.250 -1.0723 0.06125 0.05705 -0.0619 1.0000 0.0272
-16.000 -1.0805 0.05654 0.05222 -0.0648 1.0000 0.0274
-15.750 -1.0871 0.05218 0.04774 -0.0675 1.0000 0.0277
-15.500 -1.0920 0.04820 0.04363 -0.0699 1.0000 0.0279
-15.250 -1.0954 0.04460 0.03990 -0.0718 1.0000 0.0282
-15.000 -1.0974 0.04139 0.03655 -0.0733 1.0000 0.0285
-14.750 -1.0978 0.03859 0.03361 -0.0742 1.0000 0.0288
-14.500 -1.0969 0.03617 0.03105 -0.0745 1.0000 0.0292
-14.250 -1.0946 0.03411 0.02884 -0.0743 1.0000 0.0295
-14.000 -1.0911 0.03239 0.02698 -0.0736 1.0000 0.0298
-13.750 -1.0905 0.03042 0.02493 -0.0721 1.0000 0.0302
-13.500 -1.0874 0.02895 0.02342 -0.0702 1.0000 0.0306
-13.250 -1.0832 0.02788 0.02230 -0.0679 1.0000 0.0311
-13.000 -1.0806 0.02702 0.02140 -0.0647 1.0000 0.0315
-12.750 -1.0759 0.02623 0.02057 -0.0615 1.0000 0.0320
-12.500 -1.0688 0.02549 0.01976 -0.0587 1.0000 0.0326
-12.250 -1.0609 0.02480 0.01898 -0.0558 1.0000 0.0332
-12.000 -1.0521 0.02417 0.01826 -0.0529 1.0000 0.0339
-11.750 -1.0443 0.02341 0.01741 -0.0499 1.0000 0.0345
-11.500 -1.0382 0.02248 0.01647 -0.0467 1.0000 0.0352
-11.250 -1.0279 0.02187 0.01585 -0.0440 1.0000 0.0360
-11.000 -1.0161 0.02132 0.01527 -0.0415 1.0000 0.0368
-10.750 -1.0033 0.02080 0.01468 -0.0391 1.0000 0.0377
-10.500 -0.9895 0.02031 0.01411 -0.0368 1.0000 0.0386
-10.250 -0.9760 0.01971 0.01344 -0.0346 1.0000 0.0395
-10.000 -0.9485 0.01889 0.01265 -0.0353 0.9984 0.0410
-9.750 -0.9149 0.01839 0.01211 -0.0369 0.9963 0.0428
-9.500 -0.8800 0.01798 0.01161 -0.0387 0.9944 0.0446
-9.250 -0.8488 0.01715 0.01080 -0.0400 0.9922 0.0467
-9.000 -0.8164 0.01669 0.01031 -0.0413 0.9893 0.0488
-8.750 -0.7818 0.01632 0.00986 -0.0428 0.9868 0.0509
-8.500 -0.7482 0.01562 0.00920 -0.0445 0.9846 0.0539
-8.250 -0.7114 0.01526 0.00881 -0.0466 0.9830 0.0570
-8.000 -0.6802 0.01470 0.00826 -0.0476 0.9795 0.0603
-7.750 -0.6467 0.01432 0.00786 -0.0489 0.9759 0.0639
-7.500 -0.6109 0.01382 0.00737 -0.0508 0.9734 0.0684
-7.250 -0.5727 0.01346 0.00701 -0.0530 0.9716 0.0734
-7.000 -0.5345 0.01296 0.00655 -0.0554 0.9702 0.0796
-6.750 -0.5041 0.01263 0.00621 -0.0559 0.9651 0.0854
-6.500 -0.4712 0.01223 0.00586 -0.0570 0.9611 0.0927
-6.250 -0.4374 0.01183 0.00549 -0.0583 0.9579 0.1011
-6.000 -0.4042 0.01148 0.00517 -0.0594 0.9546 0.1102
-5.750 -0.3781 0.01122 0.00492 -0.0589 0.9471 0.1193
-5.500 -0.3478 0.01086 0.00462 -0.0594 0.9421 0.1312
-5.250 -0.3209 0.01057 0.00438 -0.0591 0.9352 0.1433
-5.000 -0.2935 0.01028 0.00414 -0.0588 0.9279 0.1571
-4.750 -0.2659 0.01002 0.00391 -0.0586 0.9210 0.1723
-4.500 -0.2397 0.00977 0.00372 -0.0581 0.9121 0.1886
-4.250 -0.2123 0.00953 0.00352 -0.0579 0.9043 0.2068
-4.000 -0.1858 0.00932 0.00335 -0.0574 0.8945 0.2256
-3.750 -0.1587 0.00912 0.00319 -0.0571 0.8853 0.2455
-3.500 -0.1318 0.00891 0.00304 -0.0568 0.8751 0.2666
-3.250 -0.1051 0.00872 0.00291 -0.0564 0.8642 0.2892
-3.000 -0.0778 0.00856 0.00277 -0.0561 0.8539 0.3134
-2.750 -0.0511 0.00838 0.00266 -0.0557 0.8416 0.3383
-2.500 -0.0242 0.00822 0.00256 -0.0554 0.8295 0.3659
-2.250 0.0026 0.00806 0.00245 -0.0550 0.8173 0.3957
-2.000 0.0291 0.00789 0.00236 -0.0546 0.8039 0.4302
-1.750 0.0554 0.00772 0.00230 -0.0542 0.7901 0.4708
-1.500 0.0818 0.00758 0.00225 -0.0537 0.7760 0.5153
-1.250 0.1079 0.00744 0.00221 -0.0532 0.7618 0.5581
-1.000 0.1340 0.00734 0.00218 -0.0527 0.7472 0.6001
-0.750 0.1601 0.00725 0.00217 -0.0521 0.7322 0.6405
-0.500 0.1861 0.00718 0.00217 -0.0515 0.7166 0.6796
-0.250 0.2121 0.00712 0.00219 -0.0509 0.7012 0.7170
0.000 0.2379 0.00708 0.00221 -0.0501 0.6856 0.7533
0.250 0.2635 0.00706 0.00225 -0.0494 0.6703 0.7882
0.500 0.2890 0.00707 0.00230 -0.0486 0.6551 0.8215
0.750 0.3143 0.00710 0.00237 -0.0477 0.6400 0.8528
1.000 0.3396 0.00718 0.00244 -0.0467 0.6251 0.8816
1.250 0.3655 0.00726 0.00252 -0.0459 0.6103 0.9066
1.500 0.3929 0.00738 0.00262 -0.0455 0.5958 0.9282
1.750 0.4224 0.00751 0.00271 -0.0455 0.5818 0.9455
2.000 0.4544 0.00767 0.00281 -0.0462 0.5679 0.9594
2.250 0.4881 0.00785 0.00291 -0.0472 0.5539 0.9707
2.500 0.5264 0.00802 0.00301 -0.0494 0.5392 0.9781
2.750 0.5660 0.00818 0.00312 -0.0518 0.5245 0.9839
3.000 0.6069 0.00833 0.00321 -0.0546 0.5097 0.9887
3.250 0.6460 0.00850 0.00332 -0.0570 0.4953 0.9938
3.500 0.6874 0.00865 0.00341 -0.0600 0.4804 0.9977
3.750 0.7207 0.00881 0.00350 -0.0613 0.4660 1.0000
4.000 0.7426 0.00892 0.00357 -0.0601 0.4525 1.0000
4.250 0.7645 0.00905 0.00365 -0.0590 0.4387 1.0000
4.500 0.7862 0.00919 0.00376 -0.0578 0.4248 1.0000
4.750 0.8077 0.00936 0.00387 -0.0565 0.4105 1.0000
5.000 0.8291 0.00954 0.00399 -0.0553 0.3950 1.0000
5.250 0.8505 0.00974 0.00413 -0.0540 0.3785 1.0000
5.500 0.8719 0.00996 0.00429 -0.0527 0.3612 1.0000
5.750 0.8932 0.01020 0.00446 -0.0514 0.3434 1.0000
6.000 0.9143 0.01046 0.00465 -0.0501 0.3248 1.0000
6.250 0.9352 0.01075 0.00487 -0.0488 0.3050 1.0000
6.500 0.9559 0.01109 0.00511 -0.0475 0.2846 1.0000
6.750 0.9765 0.01146 0.00538 -0.0462 0.2639 1.0000
7.000 0.9977 0.01183 0.00567 -0.0450 0.2432 1.0000
7.250 1.0185 0.01224 0.00598 -0.0438 0.2225 1.0000
7.500 1.0388 0.01270 0.00633 -0.0426 0.2025 1.0000
7.750 1.0593 0.01315 0.00670 -0.0414 0.1839 1.0000
8.000 1.0796 0.01362 0.00709 -0.0402 0.1657 1.0000
8.250 1.0994 0.01412 0.00750 -0.0389 0.1488 1.0000
8.500 1.1187 0.01464 0.00795 -0.0376 0.1336 1.0000
8.750 1.1377 0.01518 0.00841 -0.0362 0.1203 1.0000
9.000 1.1563 0.01572 0.00890 -0.0348 0.1086 1.0000
9.250 1.1743 0.01627 0.00941 -0.0333 0.0987 1.0000
9.500 1.1908 0.01687 0.00996 -0.0316 0.0902 1.0000
9.750 1.2059 0.01744 0.01051 -0.0296 0.0831 1.0000
10.000 1.2215 0.01801 0.01108 -0.0277 0.0772 1.0000
10.250 1.2339 0.01876 0.01180 -0.0255 0.0717 1.0000
10.500 1.2504 0.01931 0.01239 -0.0239 0.0675 1.0000
10.750 1.2618 0.02017 0.01322 -0.0218 0.0633 1.0000
11.000 1.2775 0.02080 0.01391 -0.0202 0.0601 1.0000
11.250 1.2898 0.02165 0.01476 -0.0184 0.0570 1.0000
11.500 1.3009 0.02259 0.01574 -0.0166 0.0543 1.0000
11.750 1.3145 0.02341 0.01661 -0.0151 0.0518 1.0000
12.000 1.3239 0.02453 0.01774 -0.0133 0.0496 1.0000
12.250 1.3325 0.02577 0.01902 -0.0116 0.0477 1.0000
12.500 1.3442 0.02682 0.02015 -0.0103 0.0459 1.0000
12.750 1.3537 0.02807 0.02145 -0.0090 0.0443 1.0000
13.000 1.3570 0.02986 0.02325 -0.0074 0.0427 1.0000
13.250 1.3659 0.03129 0.02477 -0.0063 0.0414 1.0000
13.500 1.3747 0.03277 0.02633 -0.0054 0.0400 1.0000
13.750 1.3818 0.03446 0.02808 -0.0046 0.0388 1.0000
14.000 1.3844 0.03661 0.03027 -0.0037 0.0378 1.0000
14.250 1.3829 0.03924 0.03296 -0.0030 0.0368 1.0000
14.500 1.3895 0.04118 0.03501 -0.0026 0.0359 1.0000
14.750 1.3935 0.04342 0.03734 -0.0022 0.0350 1.0000
15.000 1.3964 0.04585 0.03985 -0.0021 0.0342 1.0000
15.250 1.3977 0.04853 0.04260 -0.0021 0.0335 1.0000
15.500 1.3954 0.05165 0.04577 -0.0022 0.0328 1.0000
15.750 1.3883 0.05533 0.04950 -0.0023 0.0321 1.0000
16.000 1.3906 0.05815 0.05245 -0.0027 0.0315 1.0000
16.250 1.3909 0.06125 0.05565 -0.0032 0.0309 1.0000
16.500 1.3898 0.06454 0.05904 -0.0038 0.0303 1.0000
16.750 1.3880 0.06799 0.06258 -0.0046 0.0297 1.0000
17.000 1.3855 0.07161 0.06626 -0.0054 0.0292 1.0000
17.250 1.3817 0.07539 0.07012 -0.0064 0.0287 1.0000
17.500 1.3763 0.07935 0.07413 -0.0074 0.0283 1.0000
17.750 1.3698 0.08328 0.07809 -0.0081 0.0278 1.0000
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