NACA6409 9% (n6409-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NACA6409 9% (n6409-il) Reynolds number: 200,000 Max Cl/Cd: 87.06 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-n6409-il-200000.txt Download as CSV file: xf-n6409-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: NACA6409 9%
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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.1538 0.09258 0.08945 -0.0538 0.9758 0.0433
-8.250 -0.1400 0.08827 0.08513 -0.0581 0.9729 0.0454
-8.000 -0.2612 0.10137 0.09814 -0.0427 0.9867 0.0407
-7.750 -0.2410 0.09775 0.09450 -0.0473 0.9834 0.0424
-7.500 -0.2266 0.09436 0.09111 -0.0512 0.9766 0.0441
-7.250 -0.2094 0.09102 0.08777 -0.0591 0.9706 0.0465
-7.000 -0.1838 0.08679 0.08351 -0.0758 0.9587 0.0476
-6.750 -0.1741 0.08144 0.07818 -0.0777 0.9512 0.0483
-6.500 -0.1564 0.07801 0.07475 -0.0753 0.9483 0.0496
-6.250 -0.1298 0.07446 0.07117 -0.0790 0.9453 0.0516
-6.000 -0.1113 0.07124 0.06793 -0.0831 0.9374 0.0548
-5.500 -0.0440 0.06062 0.05715 -0.1038 0.9270 0.0611
-5.250 -0.0262 0.05817 0.05469 -0.1041 0.9197 0.0631
-5.000 0.0138 0.05397 0.05038 -0.1120 0.9167 0.0681
-4.750 0.0565 0.04741 0.04355 -0.1239 0.9102 0.0735
-4.500 0.0811 0.04531 0.04146 -0.1244 0.9053 0.0760
-4.250 0.1329 0.03985 0.03560 -0.1346 0.9026 0.0873
-4.000 0.1811 0.02831 0.02313 -0.1429 0.9005 0.0571
-3.750 0.2038 0.02449 0.01881 -0.1431 0.8919 0.0547
-3.500 0.2419 0.02164 0.01536 -0.1454 0.8886 0.0567
-3.250 0.2816 0.01944 0.01262 -0.1475 0.8862 0.0581
-3.000 0.3069 0.01794 0.01080 -0.1469 0.8781 0.0603
-2.750 0.3422 0.01697 0.00977 -0.1482 0.8737 0.0663
-2.500 0.3804 0.01583 0.00840 -0.1498 0.8706 0.0734
-2.250 0.4042 0.01530 0.00789 -0.1487 0.8609 0.0820
-2.000 0.4404 0.01457 0.00710 -0.1500 0.8565 0.0968
-1.750 0.4655 0.01417 0.00669 -0.1493 0.8468 0.1120
-1.500 0.5003 0.01360 0.00612 -0.1504 0.8414 0.1325
-1.250 0.5251 0.01332 0.00589 -0.1495 0.8310 0.1520
-1.000 0.5548 0.01298 0.00554 -0.1496 0.8227 0.1775
-0.750 0.5842 0.01265 0.00526 -0.1497 0.8136 0.2080
-0.500 0.6103 0.01239 0.00511 -0.1492 0.8029 0.2415
-0.250 0.6388 0.01211 0.00492 -0.1492 0.7935 0.2863
0.000 0.6665 0.01176 0.00474 -0.1490 0.7833 0.3500
0.250 0.6996 0.01030 0.00467 -0.1498 0.7722 1.0000
0.500 0.7269 0.01036 0.00454 -0.1495 0.7607 1.0000
0.750 0.7548 0.01043 0.00444 -0.1492 0.7498 1.0000
1.000 0.7823 0.01051 0.00436 -0.1489 0.7384 1.0000
1.250 0.8077 0.01064 0.00438 -0.1483 0.7258 1.0000
1.500 0.8336 0.01078 0.00442 -0.1478 0.7138 1.0000
1.750 0.8599 0.01093 0.00446 -0.1473 0.7023 1.0000
2.000 0.8869 0.01109 0.00450 -0.1470 0.6916 1.0000
2.250 0.9124 0.01127 0.00460 -0.1465 0.6803 1.0000
2.500 0.9376 0.01146 0.00474 -0.1459 0.6692 1.0000
2.750 0.9638 0.01167 0.00487 -0.1455 0.6594 1.0000
3.000 0.9901 0.01188 0.00502 -0.1452 0.6498 1.0000
3.250 1.0148 0.01211 0.00523 -0.1446 0.6398 1.0000
3.500 1.0414 0.01235 0.00540 -0.1443 0.6314 1.0000
3.750 1.0664 0.01259 0.00563 -0.1438 0.6223 1.0000
4.000 1.0920 0.01285 0.00589 -0.1434 0.6141 1.0000
4.250 1.1178 0.01310 0.00612 -0.1430 0.6060 1.0000
4.500 1.1427 0.01338 0.00642 -0.1425 0.5980 1.0000
4.750 1.1689 0.01364 0.00669 -0.1421 0.5905 1.0000
5.000 1.1932 0.01393 0.00703 -0.1415 0.5827 1.0000
5.250 1.2194 0.01421 0.00731 -0.1413 0.5754 1.0000
5.500 1.2432 0.01451 0.00769 -0.1406 0.5676 1.0000
5.750 1.2693 0.01480 0.00800 -0.1402 0.5603 1.0000
6.000 1.2920 0.01508 0.00838 -0.1393 0.5513 1.0000
6.250 1.3141 0.01528 0.00859 -0.1381 0.5391 1.0000
6.500 1.3321 0.01538 0.00869 -0.1360 0.5215 1.0000
6.750 1.3492 0.01550 0.00882 -0.1338 0.5031 1.0000
7.000 1.3668 0.01570 0.00901 -0.1317 0.4859 1.0000
7.250 1.3839 0.01595 0.00926 -0.1296 0.4688 1.0000
7.500 1.3994 0.01620 0.00959 -0.1273 0.4508 1.0000
7.750 1.4137 0.01649 0.00995 -0.1247 0.4305 1.0000
8.000 1.4259 0.01684 0.01032 -0.1218 0.4072 1.0000
8.250 1.4336 0.01729 0.01074 -0.1181 0.3743 1.0000
8.500 1.4307 0.01809 0.01132 -0.1126 0.3236 1.0000
8.750 1.4176 0.01967 0.01244 -0.1060 0.2503 1.0000
9.000 1.3971 0.02213 0.01428 -0.0992 0.1621 1.0000
9.250 1.3785 0.02486 0.01650 -0.0933 0.0965 1.0000
9.500 1.3681 0.02728 0.01871 -0.0887 0.0685 1.0000
9.750 1.3637 0.02941 0.02083 -0.0852 0.0574 1.0000
10.000 1.3571 0.03182 0.02325 -0.0817 0.0513 1.0000
10.250 1.3582 0.03378 0.02535 -0.0792 0.0475 1.0000
10.500 1.3586 0.03588 0.02753 -0.0770 0.0445 1.0000
10.750 1.3548 0.03846 0.03014 -0.0747 0.0421 1.0000
11.000 1.3528 0.04102 0.03278 -0.0726 0.0400 1.0000
11.250 1.3576 0.04304 0.03491 -0.0710 0.0380 1.0000
11.500 1.3620 0.04516 0.03712 -0.0695 0.0366 1.0000
11.750 1.3672 0.04728 0.03930 -0.0681 0.0352 1.0000
12.000 1.3739 0.04935 0.04142 -0.0667 0.0340 1.0000
12.250 1.3870 0.05124 0.04328 -0.0651 0.0326 1.0000
12.500 1.4057 0.05291 0.04506 -0.0638 0.0314 1.0000
12.750 1.4168 0.05475 0.04707 -0.0628 0.0304 1.0000
13.000 1.4293 0.05669 0.04918 -0.0617 0.0293 1.0000
13.250 1.4449 0.05873 0.05139 -0.0607 0.0286 1.0000
13.500 1.4592 0.06103 0.05389 -0.0597 0.0279 1.0000
13.750 1.4711 0.06365 0.05672 -0.0588 0.0275 1.0000
14.000 1.4789 0.06648 0.05973 -0.0579 0.0269 1.0000
14.250 1.4821 0.06949 0.06290 -0.0572 0.0263 1.0000
14.500 1.4881 0.07282 0.06635 -0.0566 0.0255 1.0000
14.750 1.4897 0.07801 0.07180 -0.0561 0.0250 1.0000
15.000 1.4809 0.08266 0.07671 -0.0557 0.0249 1.0000
15.250 1.4693 0.08728 0.08160 -0.0555 0.0250 1.0000
15.500 1.4556 0.09202 0.08659 -0.0558 0.0250 1.0000
15.750 1.4410 0.09684 0.09165 -0.0565 0.0251 1.0000
16.000 1.4250 0.10204 0.09709 -0.0577 0.0252 1.0000
16.250 1.4071 0.10765 0.10294 -0.0596 0.0254 1.0000
16.500 1.3827 0.11467 0.11027 -0.0626 0.0258 1.0000
16.750 1.3286 0.12794 0.12406 -0.0702 0.0271 1.0000
17.000 1.2909 0.13989 0.13631 -0.0775 0.0279 1.0000
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Polar data table (+)
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