LNV109A (lnv109a-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: LNV109A (lnv109a-il) Reynolds number: 500,000 Max Cl/Cd: 111.22 at α=11.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-lnv109a-il-500000.txt Download as CSV file: xf-lnv109a-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: LNV109A
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.2557 0.11086 0.10652 0.0101 0.4618 0.0350
-8.500 -0.2590 0.10742 0.10310 0.0062 0.4614 0.0361
-8.250 -0.2671 0.10402 0.09973 0.0019 0.4611 0.0362
-8.000 -0.2505 0.10091 0.09662 0.0024 0.4602 0.0363
-7.750 -0.2355 0.09825 0.09396 0.0025 0.4592 0.0365
-7.500 -0.2238 0.09581 0.09153 0.0021 0.4583 0.0367
-7.250 -0.2134 0.09345 0.08918 0.0014 0.4575 0.0369
-7.000 -0.2040 0.09110 0.08684 0.0005 0.4566 0.0372
-6.750 -0.1956 0.08870 0.08446 -0.0004 0.4556 0.0376
-6.500 -0.1881 0.08629 0.08206 -0.0014 0.4546 0.0381
-6.250 -0.1828 0.08381 0.07960 -0.0025 0.4537 0.0391
-6.000 -0.1985 0.07832 0.07413 -0.0144 0.4537 0.0403
-5.750 -0.1850 0.07574 0.07155 -0.0137 0.4527 0.0405
-5.500 -0.1700 0.07354 0.06934 -0.0137 0.4517 0.0406
-5.250 -0.1544 0.07142 0.06721 -0.0142 0.4508 0.0409
-5.000 -0.1383 0.06915 0.06493 -0.0156 0.4498 0.0412
-4.750 -0.1212 0.06677 0.06254 -0.0176 0.4488 0.0416
-4.500 -0.1027 0.06420 0.05994 -0.0203 0.4478 0.0423
-4.250 -0.0721 0.05611 0.05166 -0.0341 0.4470 0.0450
-4.000 -0.0533 0.05465 0.05020 -0.0341 0.4453 0.0452
-3.750 -0.0322 0.05288 0.04843 -0.0346 0.4446 0.0455
-3.500 -0.0092 0.05088 0.04642 -0.0359 0.4438 0.0460
-3.250 0.0328 0.04263 0.03777 -0.0459 0.4431 0.0498
-3.000 0.0553 0.04120 0.03636 -0.0461 0.4421 0.0501
-2.750 0.0794 0.03989 0.03505 -0.0464 0.4410 0.0504
-2.500 0.1048 0.03851 0.03365 -0.0470 0.4399 0.0510
-2.250 0.1407 0.03298 0.02763 -0.0509 0.4389 0.0555
-2.000 0.1662 0.03203 0.02671 -0.0510 0.4377 0.0559
-1.750 0.1925 0.03111 0.02578 -0.0512 0.4364 0.0566
-1.500 0.2250 0.02776 0.02190 -0.0525 0.4352 0.0615
-1.250 0.2517 0.02670 0.02086 -0.0526 0.4338 0.0621
-1.000 0.2833 0.02172 0.01496 -0.0530 0.4329 0.0554
-0.750 0.3114 0.02068 0.01389 -0.0529 0.4318 0.0542
-0.500 0.3399 0.01934 0.01235 -0.0528 0.4307 0.0533
-0.250 0.3687 0.01822 0.01098 -0.0526 0.4296 0.0526
0.000 0.3974 0.01757 0.01014 -0.0524 0.4283 0.0527
0.250 0.4256 0.01738 0.00984 -0.0522 0.4263 0.0532
0.500 0.4547 0.01693 0.00931 -0.0520 0.4255 0.0541
0.750 0.4837 0.01669 0.00898 -0.0517 0.4244 0.0550
1.000 0.5122 0.01614 0.00845 -0.0516 0.4232 0.0557
1.250 0.5408 0.01589 0.00824 -0.0514 0.4220 0.0567
1.500 0.5694 0.01572 0.00810 -0.0512 0.4206 0.0578
1.750 0.5981 0.01556 0.00795 -0.0510 0.4191 0.0591
2.000 0.6267 0.01542 0.00780 -0.0508 0.4177 0.0605
2.250 0.6552 0.01519 0.00760 -0.0506 0.4163 0.0624
2.500 0.6837 0.01509 0.00753 -0.0504 0.4150 0.0646
2.750 0.7124 0.01501 0.00745 -0.0502 0.4138 0.0668
3.000 0.7408 0.01489 0.00735 -0.0500 0.4127 0.0695
3.250 0.7694 0.01487 0.00733 -0.0498 0.4115 0.0733
3.500 0.7976 0.01495 0.00742 -0.0496 0.4100 0.0786
3.750 0.8255 0.01515 0.00768 -0.0495 0.4084 0.0863
4.000 0.8540 0.01507 0.00772 -0.0494 0.4072 0.1031
4.250 0.8811 0.01460 0.00794 -0.0493 0.4059 0.3554
4.500 0.9146 0.01339 0.00808 -0.0505 0.4042 1.0000
4.750 0.9430 0.01348 0.00815 -0.0503 0.4024 1.0000
5.000 0.9714 0.01357 0.00822 -0.0502 0.4008 1.0000
5.250 0.9997 0.01366 0.00829 -0.0500 0.3993 1.0000
5.500 1.0282 0.01371 0.00830 -0.0498 0.3979 1.0000
5.750 1.0567 0.01375 0.00829 -0.0496 0.3966 1.0000
6.000 1.0851 0.01380 0.00829 -0.0495 0.3953 1.0000
6.250 1.1133 0.01394 0.00838 -0.0493 0.3939 1.0000
6.500 1.1409 0.01424 0.00868 -0.0492 0.3921 1.0000
6.750 1.1687 0.01434 0.00884 -0.0491 0.3904 1.0000
7.000 1.1965 0.01448 0.00903 -0.0490 0.3885 1.0000
7.250 1.2243 0.01457 0.00916 -0.0489 0.3864 1.0000
7.500 1.2523 0.01461 0.00922 -0.0487 0.3845 1.0000
7.750 1.2805 0.01463 0.00923 -0.0486 0.3828 1.0000
8.000 1.3087 0.01461 0.00920 -0.0485 0.3812 1.0000
8.250 1.3370 0.01461 0.00917 -0.0483 0.3796 1.0000
8.500 1.3648 0.01475 0.00927 -0.0482 0.3778 1.0000
8.750 1.3917 0.01494 0.00955 -0.0481 0.3757 1.0000
9.000 1.4187 0.01507 0.00977 -0.0480 0.3732 1.0000
9.250 1.4461 0.01513 0.00988 -0.0479 0.3707 1.0000
9.500 1.4740 0.01508 0.00985 -0.0478 0.3682 1.0000
9.750 1.5025 0.01480 0.00953 -0.0476 0.3650 1.0000
10.000 1.5300 0.01464 0.00940 -0.0475 0.3595 1.0000
10.250 1.5576 0.01446 0.00926 -0.0474 0.3534 1.0000
10.500 1.5847 0.01443 0.00917 -0.0472 0.3489 1.0000
10.750 1.6109 0.01463 0.00948 -0.0471 0.3440 1.0000
11.000 1.6371 0.01478 0.00968 -0.0470 0.3389 1.0000
11.250 1.6628 0.01495 0.00982 -0.0468 0.3340 1.0000
11.500 1.6882 0.01523 0.01021 -0.0467 0.3282 1.0000
11.750 1.7129 0.01550 0.01049 -0.0465 0.3220 1.0000
12.000 1.7372 0.01586 0.01091 -0.0463 0.3154 1.0000
12.250 1.7602 0.01628 0.01134 -0.0460 0.3078 1.0000
12.500 1.7827 0.01677 0.01189 -0.0458 0.2997 1.0000
12.750 1.8028 0.01742 0.01253 -0.0454 0.2907 1.0000
13.000 1.8210 0.01822 0.01335 -0.0449 0.2800 1.0000
13.250 1.8360 0.01924 0.01439 -0.0443 0.2683 1.0000
13.500 1.8441 0.02071 0.01589 -0.0435 0.2558 1.0000
13.750 1.8332 0.02350 0.01874 -0.0424 0.2459 1.0000
14.000 1.7931 0.03040 0.02576 -0.0442 0.2387 1.0000
14.250 1.7602 0.03633 0.03175 -0.0449 0.2319 1.0000
14.500 1.7240 0.04243 0.03787 -0.0454 0.2245 1.0000
14.750 1.6957 0.04774 0.04320 -0.0458 0.2162 1.0000
15.000 1.6675 0.05311 0.04857 -0.0463 0.2081 1.0000
15.250 1.6464 0.05815 0.05360 -0.0470 0.1983 1.0000
15.500 1.6283 0.06300 0.05844 -0.0478 0.1880 1.0000
15.750 1.6117 0.06782 0.06322 -0.0487 0.1775 1.0000
16.000 1.5942 0.07289 0.06826 -0.0497 0.1672 1.0000
16.250 1.5790 0.07776 0.07309 -0.0507 0.1563 1.0000
16.500 1.5642 0.08276 0.07806 -0.0518 0.1460 1.0000
16.750 1.5523 0.08744 0.08270 -0.0529 0.1356 1.0000
17.000 1.5396 0.09237 0.08760 -0.0542 0.1261 1.0000
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