NACA 64A410 (naca64a410-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA 64A410 (naca64a410-il) Reynolds number: 200,000 Max Cl/Cd: 79.01 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca64a410-il-200000.txt Download as CSV file: xf-naca64a410-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA 64A410
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4418 0.08761 0.08425 -0.0479 1.0000 0.0447
-8.500 -0.4619 0.08524 0.08198 -0.0468 1.0000 0.0447
-8.250 -0.4820 0.08249 0.07926 -0.0465 1.0000 0.0447
-8.000 -0.4981 0.07976 0.07651 -0.0459 1.0000 0.0448
-7.750 -0.5109 0.07698 0.07367 -0.0453 1.0000 0.0449
-7.500 -0.5205 0.07409 0.07069 -0.0447 1.0000 0.0450
-7.250 -0.5266 0.07109 0.06754 -0.0440 1.0000 0.0451
-7.000 -0.5338 0.06380 0.06038 -0.0435 1.0000 0.0463
-6.750 -0.5131 0.06010 0.05670 -0.0457 0.9972 0.0478
-6.500 -0.4878 0.05600 0.05248 -0.0500 0.9936 0.0502
-6.250 -0.4608 0.05105 0.04723 -0.0551 0.9884 0.0546
-6.000 -0.4315 0.04492 0.04059 -0.0609 0.9842 0.0601
-5.750 -0.4052 0.04236 0.03797 -0.0628 0.9798 0.0646
-5.500 -0.3763 0.03930 0.03465 -0.0657 0.9750 0.0756
-5.250 -0.3427 0.03660 0.03171 -0.0689 0.9718 0.0877
-5.000 -0.3125 0.03419 0.02907 -0.0710 0.9675 0.1005
-4.750 -0.2835 0.03188 0.02653 -0.0725 0.9621 0.1144
-4.500 -0.2336 0.02425 0.01703 -0.0714 0.9603 0.0452
-4.250 -0.1958 0.02191 0.01435 -0.0734 0.9581 0.0450
-4.000 -0.1569 0.01978 0.01198 -0.0756 0.9564 0.0456
-3.750 -0.1292 0.01805 0.01023 -0.0757 0.9510 0.0481
-3.500 -0.0947 0.01710 0.00929 -0.0773 0.9468 0.0533
-3.250 -0.0560 0.01623 0.00833 -0.0795 0.9440 0.0574
-3.000 -0.0159 0.01520 0.00733 -0.0823 0.9419 0.0687
-2.750 0.0111 0.01474 0.00701 -0.0822 0.9345 0.0938
-2.500 0.0450 0.01271 0.00648 -0.0849 0.9314 0.4596
-2.250 0.0787 0.01228 0.00657 -0.0857 0.9283 0.6350
-2.000 0.1042 0.01225 0.00663 -0.0850 0.9210 0.6853
-1.750 0.1357 0.01213 0.00653 -0.0852 0.9159 0.7258
-1.500 0.1663 0.01198 0.00641 -0.0851 0.9107 0.7633
-1.250 0.1913 0.01182 0.00629 -0.0839 0.9025 0.7943
-1.000 0.2222 0.01150 0.00601 -0.0838 0.8984 0.8208
-0.750 0.2435 0.01136 0.00592 -0.0820 0.8889 0.8453
-0.500 0.2728 0.01109 0.00569 -0.0816 0.8845 0.8692
-0.250 0.2976 0.01100 0.00564 -0.0806 0.8761 0.8972
0.000 0.3339 0.01075 0.00539 -0.0818 0.8711 0.9271
0.250 0.3762 0.01059 0.00523 -0.0847 0.8639 0.9636
0.500 0.4215 0.01041 0.00501 -0.0884 0.8580 1.0000
0.750 0.4471 0.01040 0.00495 -0.0882 0.8498 1.0000
1.000 0.4750 0.01033 0.00482 -0.0883 0.8423 1.0000
1.250 0.5007 0.01035 0.00480 -0.0879 0.8328 1.0000
1.500 0.5299 0.01025 0.00465 -0.0879 0.8261 1.0000
1.750 0.5550 0.01026 0.00468 -0.0874 0.8153 1.0000
2.000 0.5815 0.01023 0.00463 -0.0869 0.8049 1.0000
2.250 0.6095 0.01017 0.00455 -0.0867 0.7963 1.0000
2.500 0.6360 0.01018 0.00459 -0.0864 0.7858 1.0000
2.750 0.6624 0.01016 0.00456 -0.0858 0.7733 1.0000
3.000 0.6887 0.01009 0.00447 -0.0851 0.7578 1.0000
3.250 0.7148 0.01005 0.00438 -0.0843 0.7396 1.0000
3.500 0.7396 0.01009 0.00444 -0.0835 0.7195 1.0000
3.750 0.7650 0.01015 0.00445 -0.0826 0.6979 1.0000
4.000 0.7891 0.01025 0.00455 -0.0816 0.6730 1.0000
4.250 0.8131 0.01039 0.00466 -0.0806 0.6455 1.0000
4.500 0.8359 0.01058 0.00479 -0.0794 0.6097 1.0000
4.750 0.8561 0.01093 0.00494 -0.0776 0.5529 1.0000
5.000 0.8699 0.01170 0.00521 -0.0749 0.4409 1.0000
5.250 0.8701 0.01378 0.00611 -0.0706 0.2337 1.0000
5.500 0.8786 0.01556 0.00716 -0.0680 0.1214 1.0000
5.750 0.8946 0.01674 0.00799 -0.0661 0.0654 1.0000
6.000 0.9095 0.01799 0.00919 -0.0640 0.0536 1.0000
6.250 0.9244 0.01923 0.01051 -0.0618 0.0483 1.0000
6.500 0.9414 0.02032 0.01164 -0.0601 0.0435 1.0000
6.750 0.9563 0.02188 0.01318 -0.0582 0.0404 1.0000
7.000 0.9761 0.02390 0.01523 -0.0569 0.0386 1.0000
7.250 1.0004 0.02516 0.01660 -0.0562 0.0375 1.0000
7.500 1.0264 0.02675 0.01831 -0.0557 0.0365 1.0000
7.750 1.0514 0.02829 0.02001 -0.0551 0.0349 1.0000
8.000 1.0755 0.02993 0.02181 -0.0545 0.0333 1.0000
8.250 1.1002 0.03222 0.02438 -0.0539 0.0329 1.0000
8.500 1.1223 0.03506 0.02758 -0.0527 0.0332 1.0000
8.750 1.1398 0.03879 0.03179 -0.0509 0.0345 1.0000
9.000 1.1520 0.04346 0.03691 -0.0487 0.0366 1.0000
14.250 0.6741 0.15100 0.14782 -0.0448 0.0586 1.0000
14.500 0.6721 0.15414 0.15095 -0.0462 0.0559 1.0000
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Polar data table (+)
Polar graphs
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