NACA 65-410 (naca65410-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NACA 65-410 (naca65410-il) Reynolds number: 200,000 Max Cl/Cd: 75.24 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-naca65410-il-200000.txt Download as CSV file: xf-naca65410-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.4290 0.08762 0.08411 -0.0438 1.0000 0.0406
-8.750 -0.4359 0.08361 0.08017 -0.0464 1.0000 0.0416
-8.500 -0.4481 0.07943 0.07608 -0.0494 1.0000 0.0421
-8.250 -0.4655 0.07627 0.07300 -0.0495 1.0000 0.0419
-8.000 -0.4854 0.07386 0.07063 -0.0479 1.0000 0.0418
-7.750 -0.5043 0.07167 0.06845 -0.0455 1.0000 0.0419
-7.500 -0.5240 0.06955 0.06628 -0.0434 1.0000 0.0423
-7.250 -0.5384 0.06756 0.06411 -0.0422 0.9996 0.0429
-7.000 -0.5209 0.06024 0.05635 -0.0496 0.9935 0.0440
-6.750 -0.5029 0.05504 0.05137 -0.0515 0.9901 0.0462
-6.500 -0.4769 0.05161 0.04784 -0.0551 0.9856 0.0500
-6.000 -0.4239 0.04239 0.03784 -0.0627 0.9743 0.0596
-5.750 -0.3914 0.03944 0.03471 -0.0659 0.9710 0.0655
-5.500 -0.3657 0.03601 0.03090 -0.0678 0.9647 0.0738
-5.250 -0.3341 0.03347 0.02798 -0.0703 0.9600 0.0865
-4.750 -0.2595 0.02536 0.01865 -0.0727 0.9537 0.0595
-4.500 -0.2257 0.02204 0.01468 -0.0723 0.9489 0.0454
-4.250 -0.1897 0.02020 0.01266 -0.0740 0.9457 0.0469
-4.000 -0.1509 0.01878 0.01112 -0.0761 0.9435 0.0493
-3.750 -0.1111 0.01743 0.00966 -0.0783 0.9419 0.0508
-3.500 -0.0851 0.01661 0.00879 -0.0780 0.9347 0.0532
-3.250 -0.0496 0.01567 0.00781 -0.0796 0.9312 0.0579
-3.000 -0.0127 0.01467 0.00686 -0.0817 0.9285 0.0640
-2.750 0.0150 0.01412 0.00627 -0.0819 0.9217 0.0728
-2.250 0.0712 0.01117 0.00569 -0.0830 0.9137 0.7036
-2.000 0.0910 0.01138 0.00599 -0.0805 0.9057 0.7593
-1.750 0.1144 0.01159 0.00627 -0.0782 0.9009 0.8009
-1.500 0.1314 0.01188 0.00657 -0.0748 0.8942 0.8316
-1.250 0.1501 0.01200 0.00670 -0.0718 0.8881 0.8516
-1.000 0.1768 0.01197 0.00662 -0.0708 0.8844 0.8653
-0.750 0.1988 0.01201 0.00661 -0.0698 0.8761 0.8750
-0.500 0.2263 0.01192 0.00646 -0.0694 0.8718 0.8818
-0.250 0.2507 0.01192 0.00643 -0.0688 0.8652 0.8909
0.000 0.2757 0.01186 0.00635 -0.0681 0.8595 0.8991
0.250 0.3047 0.01176 0.00621 -0.0681 0.8558 0.9073
0.500 0.3253 0.01182 0.00627 -0.0669 0.8477 0.9181
0.750 0.3523 0.01171 0.00615 -0.0664 0.8433 0.9270
1.000 0.3765 0.01170 0.00616 -0.0658 0.8370 0.9375
1.250 0.4043 0.01165 0.00613 -0.0658 0.8314 0.9482
1.500 0.4377 0.01155 0.00603 -0.0669 0.8277 0.9580
1.750 0.4720 0.01160 0.00614 -0.0686 0.8209 0.9673
2.000 0.5123 0.01155 0.00614 -0.0713 0.8162 0.9751
2.250 0.5534 0.01151 0.00615 -0.0742 0.8117 0.9829
2.500 0.5950 0.01151 0.00622 -0.0774 0.8040 0.9903
2.750 0.6370 0.01135 0.00614 -0.0803 0.7964 0.9984
3.000 0.6577 0.01111 0.00590 -0.0787 0.7823 1.0000
3.250 0.6746 0.01083 0.00561 -0.0761 0.7630 1.0000
3.500 0.6965 0.01045 0.00516 -0.0742 0.7372 1.0000
3.750 0.7194 0.01022 0.00488 -0.0727 0.7070 1.0000
4.000 0.7437 0.01015 0.00482 -0.0717 0.6767 1.0000
4.250 0.7667 0.01019 0.00476 -0.0704 0.6298 1.0000
4.500 0.7744 0.01108 0.00473 -0.0662 0.4344 1.0000
4.750 0.7618 0.01457 0.00621 -0.0606 0.0953 1.0000
5.000 0.7787 0.01582 0.00726 -0.0590 0.0652 1.0000
5.250 0.7972 0.01684 0.00829 -0.0577 0.0548 1.0000
5.500 0.8170 0.01777 0.00928 -0.0565 0.0505 1.0000
5.750 0.8365 0.01880 0.01033 -0.0553 0.0468 1.0000
6.000 0.8557 0.02014 0.01164 -0.0540 0.0440 1.0000
6.250 0.8784 0.02185 0.01337 -0.0533 0.0413 1.0000
6.500 0.9046 0.02311 0.01474 -0.0530 0.0395 1.0000
6.750 0.9331 0.02479 0.01654 -0.0530 0.0384 1.0000
7.000 0.9628 0.02685 0.01878 -0.0531 0.0379 1.0000
7.250 0.9913 0.02925 0.02143 -0.0529 0.0378 1.0000
7.500 1.0159 0.03134 0.02377 -0.0523 0.0364 1.0000
7.750 1.0395 0.03467 0.02753 -0.0512 0.0374 1.0000
8.000 1.0587 0.03957 0.03284 -0.0499 0.0406 1.0000
10.000 1.0890 0.07863 0.07447 -0.0335 0.0539 1.0000
10.250 1.0631 0.07925 0.07541 -0.0290 0.0533 1.0000
10.500 1.0350 0.08163 0.07799 -0.0258 0.0530 1.0000
10.750 1.0088 0.08534 0.08187 -0.0248 0.0527 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NACA 65-410 (naca65410-il)