NACA 65-410 (naca65410-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 65-410 (naca65410-il) Reynolds number: 100,000 Max Cl/Cd: 52.64 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca65410-il-100000-n5.txt Download as CSV file: xf-naca65410-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 65-410
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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4457 0.11242 0.10724 -0.0422 1.0000 0.0401
-10.250 -0.4293 0.10825 0.10305 -0.0369 1.0000 0.0440
-10.000 -0.4265 0.10492 0.09976 -0.0379 1.0000 0.0452
-9.750 -0.4254 0.10160 0.09645 -0.0390 1.0000 0.0481
-9.500 -0.4271 0.09792 0.09284 -0.0409 1.0000 0.0500
-9.000 -0.3567 0.07804 0.07341 -0.0455 1.0000 0.0362
-8.750 -0.3639 0.07374 0.06918 -0.0461 1.0000 0.0346
-8.500 -0.4453 0.08055 0.07577 -0.0474 1.0000 0.0362
-8.250 -0.4575 0.07671 0.07203 -0.0485 1.0000 0.0348
-8.000 -0.4757 0.07330 0.06871 -0.0488 1.0000 0.0339
-7.750 -0.4933 0.06961 0.06504 -0.0484 1.0000 0.0325
-7.500 -0.5194 0.06462 0.05970 -0.0482 1.0000 0.0282
-7.250 -0.5231 0.06135 0.05642 -0.0463 0.9998 0.0274
-7.000 -0.5060 0.05557 0.05039 -0.0507 0.9930 0.0269
-6.750 -0.4858 0.05006 0.04451 -0.0546 0.9863 0.0267
-6.500 -0.4642 0.04514 0.03915 -0.0573 0.9793 0.0266
-6.000 -0.4148 0.03711 0.03015 -0.0619 0.9672 0.0302
-5.750 -0.3838 0.03371 0.02626 -0.0640 0.9632 0.0308
-5.500 -0.3575 0.03098 0.02308 -0.0646 0.9565 0.0313
-5.250 -0.3252 0.02850 0.02015 -0.0661 0.9524 0.0323
-5.000 -0.2932 0.02678 0.01809 -0.0674 0.9481 0.0354
-4.750 -0.2632 0.02516 0.01607 -0.0679 0.9424 0.0375
-4.500 -0.2290 0.02352 0.01411 -0.0691 0.9388 0.0387
-4.250 -0.1935 0.02220 0.01255 -0.0705 0.9360 0.0400
-4.000 -0.1688 0.02083 0.01124 -0.0704 0.9290 0.0439
-3.750 -0.1368 0.01989 0.01026 -0.0714 0.9248 0.0477
-3.500 -0.1064 0.01903 0.00929 -0.0720 0.9201 0.0506
-3.250 -0.0787 0.01837 0.00853 -0.0722 0.9137 0.0538
-3.000 -0.0462 0.01768 0.00780 -0.0735 0.9096 0.0636
-2.750 -0.0188 0.01713 0.00722 -0.0736 0.9032 0.0750
-2.500 0.0106 0.01621 0.00662 -0.0745 0.8979 0.1466
-2.250 0.0272 0.01436 0.00697 -0.0724 0.8934 0.6818
-2.000 0.0442 0.01456 0.00727 -0.0691 0.8855 0.7518
-1.750 0.0631 0.01479 0.00755 -0.0655 0.8807 0.8045
-1.500 0.0775 0.01498 0.00772 -0.0617 0.8728 0.8367
-1.250 0.1054 0.01494 0.00753 -0.0614 0.8681 0.8481
-1.000 0.1323 0.01491 0.00738 -0.0613 0.8623 0.8569
-0.750 0.1593 0.01488 0.00726 -0.0612 0.8563 0.8662
-0.500 0.1899 0.01481 0.00708 -0.0617 0.8523 0.8740
-0.250 0.2134 0.01484 0.00707 -0.0610 0.8451 0.8839
0.000 0.2423 0.01480 0.00697 -0.0612 0.8403 0.8931
0.250 0.2703 0.01477 0.00691 -0.0613 0.8351 0.9023
0.500 0.2963 0.01479 0.00692 -0.0610 0.8287 0.9130
0.750 0.3274 0.01474 0.00684 -0.0617 0.8245 0.9234
1.000 0.3551 0.01478 0.00690 -0.0619 0.8181 0.9346
1.250 0.3876 0.01477 0.00692 -0.0630 0.8129 0.9453
1.500 0.4245 0.01472 0.00689 -0.0649 0.8093 0.9553
1.750 0.4577 0.01482 0.00707 -0.0666 0.8023 0.9677
2.000 0.4966 0.01482 0.00712 -0.0691 0.7976 0.9794
2.250 0.5335 0.01487 0.00728 -0.0713 0.7922 0.9996
2.500 0.5563 0.01503 0.00749 -0.0708 0.7850 1.0000
2.750 0.5845 0.01511 0.00764 -0.0711 0.7797 1.0000
3.000 0.6084 0.01532 0.00794 -0.0708 0.7714 1.0000
3.250 0.6373 0.01539 0.00813 -0.0711 0.7645 1.0000
3.500 0.6641 0.01548 0.00834 -0.0710 0.7552 1.0000
3.750 0.6925 0.01526 0.00820 -0.0704 0.7397 1.0000
4.000 0.7169 0.01474 0.00770 -0.0685 0.7054 1.0000
4.250 0.7380 0.01424 0.00703 -0.0656 0.6391 1.0000
4.500 0.7559 0.01436 0.00680 -0.0629 0.5374 1.0000
4.750 0.7628 0.01573 0.00702 -0.0591 0.3346 1.0000
5.000 0.7638 0.01822 0.00820 -0.0557 0.1210 1.0000
5.250 0.7781 0.01967 0.00922 -0.0540 0.0674 1.0000
5.500 0.7972 0.02064 0.01024 -0.0527 0.0561 1.0000
5.750 0.8156 0.02165 0.01129 -0.0514 0.0496 1.0000
6.000 0.8345 0.02257 0.01228 -0.0503 0.0437 1.0000
6.250 0.8496 0.02392 0.01363 -0.0487 0.0403 1.0000
6.500 0.8686 0.02503 0.01488 -0.0474 0.0387 1.0000
6.750 0.8890 0.02633 0.01627 -0.0464 0.0371 1.0000
7.000 0.9122 0.02780 0.01788 -0.0458 0.0356 1.0000
7.250 0.9373 0.02932 0.01949 -0.0455 0.0338 1.0000
7.500 0.9613 0.03080 0.02106 -0.0453 0.0316 1.0000
7.750 0.9864 0.03286 0.02317 -0.0453 0.0296 1.0000
8.000 1.0146 0.03598 0.02650 -0.0457 0.0288 1.0000
8.250 1.0374 0.03835 0.02921 -0.0451 0.0284 1.0000
8.500 1.0571 0.04083 0.03207 -0.0442 0.0281 1.0000
8.750 1.0736 0.04357 0.03521 -0.0429 0.0278 1.0000
9.000 1.0865 0.04654 0.03861 -0.0412 0.0277 1.0000
9.250 1.0954 0.04975 0.04224 -0.0393 0.0276 1.0000
9.500 1.1004 0.05313 0.04602 -0.0371 0.0275 1.0000
9.750 1.1010 0.05639 0.04968 -0.0347 0.0272 1.0000
10.000 1.0969 0.05962 0.05328 -0.0319 0.0268 1.0000
10.250 1.0871 0.06271 0.05670 -0.0288 0.0263 1.0000
10.500 1.0734 0.06598 0.06025 -0.0259 0.0260 1.0000
10.750 1.0574 0.06960 0.06411 -0.0238 0.0259 1.0000
11.000 1.0394 0.07366 0.06839 -0.0226 0.0258 1.0000
11.250 1.0198 0.07828 0.07322 -0.0225 0.0258 1.0000
11.500 0.9989 0.08356 0.07868 -0.0236 0.0259 1.0000
11.750 0.9774 0.08961 0.08489 -0.0260 0.0261 1.0000
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Polar data table (+)
Polar graphs
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