NACA 64A410 (naca64a410-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: NACA 64A410 (naca64a410-il) Reynolds number: 100,000 Max Cl/Cd: 55.55 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca64a410-il-100000-n5.txt Download as CSV file: xf-naca64a410-il-100000-n5.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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4247 0.09447 0.08944 -0.0412 1.0000 0.0338
-8.750 -0.4492 0.08219 0.07735 -0.0491 1.0000 0.0275
-8.500 -0.4594 0.07920 0.07444 -0.0485 1.0000 0.0272
-8.250 -0.4737 0.07611 0.07144 -0.0483 1.0000 0.0270
-8.000 -0.4864 0.07274 0.06810 -0.0483 1.0000 0.0268
-7.750 -0.4982 0.06935 0.06470 -0.0479 1.0000 0.0267
-7.500 -0.5082 0.06570 0.06100 -0.0475 1.0000 0.0266
-7.250 -0.5153 0.06176 0.05695 -0.0472 1.0000 0.0266
-7.000 -0.5036 0.05547 0.05028 -0.0516 0.9958 0.0271
-6.750 -0.4824 0.04952 0.04377 -0.0561 0.9901 0.0276
-6.500 -0.4583 0.04439 0.03815 -0.0595 0.9857 0.0276
-6.250 -0.4347 0.04001 0.03324 -0.0616 0.9803 0.0276
-6.000 -0.4064 0.03586 0.02851 -0.0639 0.9764 0.0279
-5.750 -0.3807 0.03258 0.02489 -0.0653 0.9717 0.0289
-5.500 -0.3510 0.03084 0.02297 -0.0670 0.9674 0.0314
-5.250 -0.3172 0.02856 0.02019 -0.0688 0.9644 0.0334
-5.000 -0.2887 0.02652 0.01771 -0.0692 0.9593 0.0344
-4.750 -0.2564 0.02480 0.01560 -0.0701 0.9552 0.0357
-4.500 -0.2219 0.02333 0.01387 -0.0716 0.9522 0.0388
-4.250 -0.1909 0.02204 0.01252 -0.0726 0.9481 0.0417
-4.000 -0.1617 0.02100 0.01139 -0.0730 0.9428 0.0442
-3.750 -0.1281 0.02008 0.01035 -0.0743 0.9390 0.0475
-3.500 -0.0928 0.01911 0.00936 -0.0762 0.9362 0.0546
-2.750 -0.0003 0.01722 0.00760 -0.0787 0.9209 0.1312
-2.500 0.0231 0.01573 0.00727 -0.0791 0.9139 0.3792
-2.250 0.0512 0.01518 0.00735 -0.0789 0.9093 0.5831
-2.000 0.0763 0.01508 0.00741 -0.0779 0.9030 0.6648
-1.750 0.1016 0.01501 0.00743 -0.0768 0.8967 0.7240
-1.500 0.1311 0.01488 0.00731 -0.0765 0.8927 0.7682
-1.250 0.1537 0.01482 0.00723 -0.0752 0.8843 0.7951
-1.000 0.1842 0.01469 0.00705 -0.0754 0.8796 0.8168
-0.750 0.2095 0.01461 0.00698 -0.0746 0.8723 0.8396
-0.500 0.2395 0.01448 0.00685 -0.0747 0.8667 0.8658
-0.250 0.2740 0.01437 0.00673 -0.0758 0.8619 0.8956
0.000 0.3120 0.01430 0.00666 -0.0779 0.8545 0.9400
0.250 0.3560 0.01412 0.00642 -0.0812 0.8493 1.0000
0.500 0.3805 0.01417 0.00639 -0.0807 0.8387 1.0000
0.750 0.4084 0.01412 0.00628 -0.0808 0.8292 1.0000
1.000 0.4381 0.01402 0.00613 -0.0810 0.8202 1.0000
1.250 0.4634 0.01404 0.00611 -0.0805 0.8087 1.0000
1.500 0.4903 0.01405 0.00610 -0.0802 0.7987 1.0000
1.750 0.5197 0.01402 0.00606 -0.0804 0.7915 1.0000
2.000 0.5453 0.01414 0.00621 -0.0801 0.7818 1.0000
2.250 0.5735 0.01417 0.00625 -0.0801 0.7736 1.0000
2.500 0.6013 0.01419 0.00629 -0.0799 0.7640 1.0000
2.750 0.6278 0.01427 0.00644 -0.0796 0.7533 1.0000
3.000 0.6556 0.01433 0.00655 -0.0795 0.7440 1.0000
3.250 0.6836 0.01438 0.00666 -0.0793 0.7343 1.0000
3.500 0.7098 0.01449 0.00684 -0.0789 0.7220 1.0000
3.750 0.7367 0.01449 0.00691 -0.0783 0.7053 1.0000
4.000 0.7610 0.01451 0.00693 -0.0772 0.6790 1.0000
4.250 0.7851 0.01453 0.00691 -0.0758 0.6460 1.0000
4.500 0.8074 0.01465 0.00696 -0.0743 0.6038 1.0000
4.750 0.8288 0.01492 0.00712 -0.0727 0.5511 1.0000
5.000 0.8489 0.01535 0.00735 -0.0710 0.4861 1.0000
5.250 0.8596 0.01649 0.00774 -0.0679 0.3451 1.0000
5.500 0.8660 0.01833 0.00869 -0.0649 0.2017 1.0000
5.750 0.8775 0.01988 0.00969 -0.0628 0.1272 1.0000
6.000 0.8945 0.02092 0.01066 -0.0612 0.0862 1.0000
6.250 0.9106 0.02202 0.01148 -0.0596 0.0590 1.0000
6.500 0.9250 0.02328 0.01269 -0.0576 0.0510 1.0000
6.750 0.9410 0.02435 0.01390 -0.0558 0.0449 1.0000
7.000 0.9531 0.02581 0.01539 -0.0537 0.0406 1.0000
7.250 0.9689 0.02703 0.01672 -0.0519 0.0384 1.0000
7.500 0.9859 0.02830 0.01816 -0.0503 0.0364 1.0000
7.750 1.0044 0.02972 0.01967 -0.0490 0.0347 1.0000
8.000 1.0246 0.03124 0.02128 -0.0480 0.0330 1.0000
8.250 1.0449 0.03289 0.02296 -0.0472 0.0310 1.0000
8.500 1.0678 0.03505 0.02521 -0.0468 0.0291 1.0000
8.750 1.0907 0.03693 0.02740 -0.0461 0.0282 1.0000
9.000 1.1123 0.03917 0.02995 -0.0452 0.0274 1.0000
9.250 1.1310 0.04167 0.03280 -0.0441 0.0267 1.0000
9.500 1.1459 0.04440 0.03592 -0.0425 0.0262 1.0000
9.750 1.1563 0.04728 0.03919 -0.0405 0.0257 1.0000
10.000 1.1626 0.04999 0.04226 -0.0382 0.0250 1.0000
10.250 1.1663 0.05247 0.04501 -0.0359 0.0241 1.0000
10.500 1.1681 0.05472 0.04746 -0.0335 0.0232 1.0000
10.750 1.1654 0.05723 0.05018 -0.0308 0.0227 1.0000
11.000 1.1586 0.06018 0.05341 -0.0280 0.0224 1.0000
11.250 1.1479 0.06347 0.05697 -0.0254 0.0222 1.0000
11.500 1.1343 0.06705 0.06081 -0.0233 0.0222 1.0000
11.750 1.1182 0.07099 0.06500 -0.0217 0.0221 1.0000
12.000 1.0996 0.07540 0.06966 -0.0209 0.0221 1.0000
12.250 1.0786 0.08044 0.07496 -0.0212 0.0222 1.0000
12.500 1.0544 0.08644 0.08120 -0.0227 0.0224 1.0000
12.750 1.0269 0.09381 0.08877 -0.0259 0.0226 1.0000
13.000 0.9836 0.10599 0.10122 -0.0337 0.0233 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 64A410 (naca64a410-il)