NACA 2410 (naca2410-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 2410 (naca2410-il) Reynolds number: 100,000 Max Cl/Cd: 49.94 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca2410-il-100000-n5.txt Download as CSV file: xf-naca2410-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 2410
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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5629 0.09185 0.08660 -0.0254 1.0000 0.0367
-10.000 -0.5764 0.08412 0.07895 -0.0302 1.0000 0.0370
-9.750 -0.5963 0.07438 0.06927 -0.0370 1.0000 0.0369
-9.500 -0.6274 0.06309 0.05795 -0.0469 1.0000 0.0361
-9.250 -0.6545 0.05546 0.05008 -0.0504 1.0000 0.0359
-9.000 -0.6728 0.04909 0.04331 -0.0511 1.0000 0.0364
-8.750 -0.6827 0.04362 0.03725 -0.0503 1.0000 0.0373
-8.500 -0.6828 0.03937 0.03243 -0.0488 1.0000 0.0383
-8.250 -0.6713 0.03713 0.03002 -0.0476 1.0000 0.0394
-8.000 -0.6569 0.03559 0.02835 -0.0464 1.0000 0.0411
-7.750 -0.6424 0.03385 0.02637 -0.0451 1.0000 0.0434
-7.500 -0.6282 0.03157 0.02363 -0.0436 1.0000 0.0457
-7.250 -0.6120 0.02947 0.02100 -0.0421 1.0000 0.0476
-7.000 -0.5941 0.02803 0.01957 -0.0410 1.0000 0.0499
-6.750 -0.5750 0.02698 0.01838 -0.0399 1.0000 0.0525
-6.500 -0.5553 0.02566 0.01681 -0.0387 1.0000 0.0549
-6.250 -0.5347 0.02454 0.01539 -0.0376 1.0000 0.0579
-6.000 -0.5143 0.02339 0.01418 -0.0366 1.0000 0.0606
-5.750 -0.4933 0.02250 0.01324 -0.0356 1.0000 0.0632
-5.500 -0.4718 0.02165 0.01227 -0.0346 1.0000 0.0660
-5.250 -0.4499 0.02096 0.01141 -0.0336 1.0000 0.0700
-5.000 -0.4283 0.02016 0.01062 -0.0327 1.0000 0.0736
-4.750 -0.4063 0.01953 0.00996 -0.0319 1.0000 0.0776
-4.500 -0.3839 0.01895 0.00928 -0.0310 1.0000 0.0824
-4.250 -0.3615 0.01836 0.00872 -0.0304 1.0000 0.0885
-4.000 -0.3246 0.01779 0.00816 -0.0326 0.9951 0.1017
-3.750 -0.2880 0.01723 0.00764 -0.0347 0.9893 0.1204
-3.500 -0.2504 0.01673 0.00723 -0.0371 0.9839 0.1467
-3.250 -0.2148 0.01628 0.00692 -0.0390 0.9771 0.1840
-3.000 -0.1789 0.01585 0.00668 -0.0410 0.9707 0.2338
-2.750 -0.1431 0.01538 0.00649 -0.0430 0.9639 0.2979
-2.500 -0.1091 0.01493 0.00631 -0.0445 0.9564 0.3660
-2.250 -0.0732 0.01445 0.00614 -0.0463 0.9498 0.4474
-2.000 -0.0413 0.01397 0.00606 -0.0470 0.9415 0.5472
-1.750 -0.0087 0.01353 0.00600 -0.0474 0.9343 0.6580
-1.500 0.0191 0.01321 0.00600 -0.0464 0.9246 0.7625
-1.250 0.0574 0.01301 0.00599 -0.0473 0.9182 0.8639
-1.000 0.1046 0.01292 0.00589 -0.0506 0.9099 0.9393
-0.750 0.1598 0.01281 0.00568 -0.0560 0.9033 0.9868
-0.500 0.1992 0.01272 0.00549 -0.0583 0.8913 1.0000
-0.250 0.2290 0.01266 0.00533 -0.0586 0.8774 1.0000
0.000 0.2582 0.01260 0.00519 -0.0587 0.8630 1.0000
0.250 0.2867 0.01256 0.00506 -0.0586 0.8480 1.0000
0.500 0.3148 0.01254 0.00496 -0.0584 0.8324 1.0000
0.750 0.3424 0.01252 0.00488 -0.0581 0.8162 1.0000
1.000 0.3697 0.01253 0.00481 -0.0577 0.7994 1.0000
1.250 0.3969 0.01255 0.00476 -0.0572 0.7824 1.0000
1.500 0.4233 0.01260 0.00476 -0.0566 0.7644 1.0000
1.750 0.4493 0.01268 0.00478 -0.0560 0.7456 1.0000
2.000 0.4754 0.01278 0.00482 -0.0553 0.7267 1.0000
2.250 0.5014 0.01289 0.00488 -0.0546 0.7078 1.0000
2.500 0.5273 0.01303 0.00494 -0.0540 0.6889 1.0000
2.750 0.5526 0.01319 0.00508 -0.0532 0.6686 1.0000
3.000 0.5779 0.01336 0.00521 -0.0525 0.6485 1.0000
3.250 0.6033 0.01356 0.00534 -0.0517 0.6286 1.0000
3.500 0.6282 0.01377 0.00554 -0.0510 0.6074 1.0000
3.750 0.6531 0.01401 0.00573 -0.0502 0.5860 1.0000
4.000 0.6776 0.01426 0.00594 -0.0493 0.5631 1.0000
4.250 0.7017 0.01453 0.00616 -0.0484 0.5381 1.0000
4.500 0.7254 0.01482 0.00641 -0.0474 0.5112 1.0000
4.750 0.7490 0.01513 0.00668 -0.0465 0.4843 1.0000
5.000 0.7721 0.01547 0.00699 -0.0455 0.4539 1.0000
5.250 0.7935 0.01589 0.00726 -0.0442 0.4118 1.0000
5.500 0.8139 0.01641 0.00757 -0.0429 0.3591 1.0000
5.750 0.8340 0.01705 0.00797 -0.0416 0.3065 1.0000
6.000 0.8542 0.01775 0.00850 -0.0405 0.2573 1.0000
6.250 0.8733 0.01862 0.00912 -0.0393 0.2071 1.0000
6.500 0.8916 0.01962 0.00986 -0.0380 0.1598 1.0000
6.750 0.9098 0.02067 0.01070 -0.0368 0.1232 1.0000
7.000 0.9281 0.02169 0.01164 -0.0355 0.1013 1.0000
7.250 0.9462 0.02272 0.01263 -0.0341 0.0883 1.0000
7.500 0.9639 0.02375 0.01367 -0.0327 0.0798 1.0000
7.750 0.9816 0.02476 0.01476 -0.0313 0.0738 1.0000
8.000 0.9992 0.02576 0.01581 -0.0299 0.0685 1.0000
8.250 1.0151 0.02693 0.01701 -0.0284 0.0645 1.0000
8.500 1.0329 0.02800 0.01822 -0.0270 0.0615 1.0000
8.750 1.0501 0.02916 0.01947 -0.0256 0.0587 1.0000
9.000 1.0666 0.03036 0.02070 -0.0242 0.0559 1.0000
9.250 1.0829 0.03180 0.02217 -0.0229 0.0533 1.0000
9.500 1.1010 0.03312 0.02369 -0.0217 0.0509 1.0000
9.750 1.1181 0.03451 0.02527 -0.0204 0.0485 1.0000
10.000 1.1333 0.03586 0.02669 -0.0191 0.0461 1.0000
10.250 1.1484 0.03764 0.02846 -0.0180 0.0439 1.0000
10.500 1.1629 0.03946 0.03056 -0.0166 0.0422 1.0000
10.750 1.1744 0.04128 0.03267 -0.0149 0.0402 1.0000
11.000 1.1824 0.04300 0.03461 -0.0129 0.0383 1.0000
11.250 1.1894 0.04479 0.03655 -0.0110 0.0368 1.0000
11.500 1.1961 0.04679 0.03867 -0.0093 0.0357 1.0000
11.750 1.2005 0.04945 0.04144 -0.0077 0.0345 1.0000
12.000 1.1949 0.05210 0.04448 -0.0053 0.0336 1.0000
12.250 1.1871 0.05512 0.04786 -0.0035 0.0326 1.0000
12.500 1.1776 0.05846 0.05150 -0.0023 0.0318 1.0000
12.750 1.1663 0.06218 0.05550 -0.0017 0.0311 1.0000
13.000 1.1527 0.06644 0.06002 -0.0019 0.0307 1.0000
13.250 1.1362 0.07139 0.06523 -0.0030 0.0304 1.0000
13.500 1.1164 0.07721 0.07130 -0.0051 0.0303 1.0000
13.750 1.0921 0.08427 0.07861 -0.0086 0.0303 1.0000
14.000 1.0615 0.09324 0.08783 -0.0140 0.0306 1.0000
14.250 1.0213 0.10540 0.10023 -0.0221 0.0312 1.0000
14.500 0.9700 0.12260 0.11756 -0.0334 0.0326 1.0000
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Polar data table (+)
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