LNV109A (lnv109a-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: LNV109A (lnv109a-il) Reynolds number: 200,000 Max Cl/Cd: 58.31 at α=9.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-lnv109a-il-200000-n5.txt Download as CSV file: xf-lnv109a-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2440 0.10822 0.10244 0.0073 0.4638 0.0445
-8.000 -0.2430 0.10541 0.09965 0.0045 0.4631 0.0447
-7.750 -0.2409 0.10254 0.09682 0.0021 0.4623 0.0448
-7.500 -0.2274 0.09949 0.09379 0.0019 0.4611 0.0450
-7.250 -0.2147 0.09680 0.09112 0.0016 0.4599 0.0452
-7.000 -0.2039 0.09428 0.08861 0.0009 0.4588 0.0456
-6.750 -0.1946 0.09182 0.08617 0.0000 0.4579 0.0460
-6.500 -0.1864 0.08936 0.08374 -0.0011 0.4569 0.0466
-6.250 -0.1794 0.08691 0.08132 -0.0022 0.4560 0.0473
-6.000 -0.1752 0.08460 0.07904 -0.0033 0.4551 0.0479
-5.750 -0.1717 0.08180 0.07624 -0.0070 0.4544 0.0492
-5.500 -0.1651 0.07739 0.07180 -0.0162 0.4538 0.0497
-5.250 -0.1502 0.07509 0.06952 -0.0151 0.4527 0.0500
-5.000 -0.1345 0.07284 0.06727 -0.0154 0.4516 0.0504
-4.750 -0.1182 0.07033 0.06474 -0.0172 0.4505 0.0509
-4.500 -0.1006 0.06762 0.06200 -0.0198 0.4494 0.0515
-4.000 -0.0545 0.05626 0.05033 -0.0340 0.4477 0.0450
-3.750 -0.0309 0.05333 0.04729 -0.0364 0.4467 0.0445
-3.500 -0.0021 0.04846 0.04220 -0.0415 0.4458 0.0447
-3.250 0.0232 0.04593 0.03958 -0.0433 0.4449 0.0444
-3.000 0.0506 0.04289 0.03643 -0.0456 0.4439 0.0442
-2.750 0.0800 0.03916 0.03250 -0.0483 0.4428 0.0440
-2.500 0.1126 0.03246 0.02515 -0.0520 0.4418 0.0446
-2.250 0.1400 0.03109 0.02367 -0.0526 0.4403 0.0453
-2.000 0.1678 0.02987 0.02234 -0.0530 0.4387 0.0459
-1.750 0.1966 0.02770 0.01985 -0.0535 0.4372 0.0463
-1.500 0.2252 0.02602 0.01786 -0.0538 0.4358 0.0468
-1.250 0.2539 0.02463 0.01617 -0.0540 0.4345 0.0475
-1.000 0.2828 0.02347 0.01467 -0.0540 0.4333 0.0487
-0.750 0.3116 0.02254 0.01341 -0.0539 0.4322 0.0499
-0.500 0.3398 0.02208 0.01290 -0.0537 0.4310 0.0506
-0.250 0.3682 0.02163 0.01235 -0.0535 0.4298 0.0512
0.000 0.3966 0.02121 0.01180 -0.0533 0.4286 0.0520
0.250 0.4251 0.02084 0.01129 -0.0531 0.4275 0.0530
0.500 0.4534 0.02057 0.01090 -0.0529 0.4263 0.0541
0.750 0.4818 0.02038 0.01073 -0.0528 0.4249 0.0556
1.000 0.5100 0.02030 0.01075 -0.0527 0.4233 0.0570
1.250 0.5382 0.02021 0.01069 -0.0526 0.4215 0.0585
1.500 0.5663 0.02008 0.01059 -0.0525 0.4197 0.0599
1.750 0.5944 0.01997 0.01049 -0.0523 0.4179 0.0613
2.000 0.6223 0.01989 0.01049 -0.0521 0.4163 0.0632
2.250 0.6503 0.01988 0.01050 -0.0520 0.4150 0.0661
2.500 0.6782 0.01983 0.01049 -0.0518 0.4137 0.0689
2.750 0.7062 0.01980 0.01048 -0.0516 0.4125 0.0719
3.000 0.7343 0.01975 0.01043 -0.0513 0.4114 0.0757
3.250 0.7623 0.01973 0.01041 -0.0511 0.4103 0.0818
3.500 0.7903 0.01973 0.01042 -0.0508 0.4092 0.0899
3.750 0.8175 0.01997 0.01081 -0.0508 0.4074 0.1036
4.000 0.8442 0.02022 0.01132 -0.0508 0.4051 0.1414
4.250 0.8698 0.02004 0.01182 -0.0508 0.4029 0.3662
4.750 0.9319 0.01938 0.01227 -0.0519 0.3990 1.0000
5.000 0.9593 0.01960 0.01245 -0.0517 0.3975 1.0000
5.250 0.9868 0.01979 0.01259 -0.0514 0.3962 1.0000
5.500 1.0145 0.01992 0.01266 -0.0512 0.3950 1.0000
5.750 1.0423 0.02001 0.01269 -0.0509 0.3939 1.0000
6.000 1.0701 0.02012 0.01273 -0.0506 0.3928 1.0000
6.250 1.0945 0.02093 0.01370 -0.0507 0.3898 1.0000
6.500 1.1193 0.02159 0.01445 -0.0507 0.3868 1.0000
6.750 1.1453 0.02196 0.01487 -0.0506 0.3844 1.0000
7.000 1.1717 0.02221 0.01513 -0.0504 0.3826 1.0000
7.250 1.1985 0.02236 0.01528 -0.0501 0.3810 1.0000
7.500 1.2258 0.02241 0.01532 -0.0498 0.3797 1.0000
7.750 1.2533 0.02241 0.01530 -0.0495 0.3785 1.0000
8.000 1.2810 0.02242 0.01527 -0.0492 0.3774 1.0000
8.250 1.2992 0.02390 0.01702 -0.0493 0.3725 1.0000
8.500 1.3226 0.02445 0.01766 -0.0492 0.3697 1.0000
8.750 1.3478 0.02469 0.01794 -0.0489 0.3675 1.0000
9.000 1.3742 0.02472 0.01799 -0.0486 0.3658 1.0000
9.250 1.4015 0.02464 0.01790 -0.0482 0.3644 1.0000
9.500 1.4291 0.02451 0.01776 -0.0478 0.3631 1.0000
9.750 1.4413 0.02631 0.01984 -0.0478 0.3579 1.0000
10.000 1.4613 0.02700 0.02062 -0.0475 0.3546 1.0000
10.250 1.4860 0.02708 0.02074 -0.0471 0.3523 1.0000
10.500 1.5134 0.02683 0.02049 -0.0467 0.3503 1.0000
10.750 1.5396 0.02665 0.02032 -0.0462 0.3475 1.0000
11.000 1.5406 0.02894 0.02285 -0.0460 0.3400 1.0000
11.250 1.5780 0.02738 0.02117 -0.0454 0.3352 1.0000
11.500 1.4561 0.04239 0.03653 -0.0490 0.3227 1.0000
11.750 1.4768 0.04251 0.03665 -0.0485 0.3179 1.0000
12.250 1.3860 0.05798 0.05220 -0.0514 0.2965 1.0000
12.500 1.4324 0.05502 0.04921 -0.0501 0.2938 1.0000
12.750 1.3908 0.06263 0.05688 -0.0516 0.2834 1.0000
13.000 1.4329 0.06006 0.05429 -0.0503 0.2798 1.0000
13.250 1.4038 0.06637 0.06065 -0.0516 0.2703 1.0000
13.500 1.4375 0.06477 0.05901 -0.0505 0.2655 1.0000
13.750 1.4190 0.07006 0.06436 -0.0517 0.2565 1.0000
14.000 1.4487 0.06890 0.06313 -0.0507 0.2507 1.0000
14.250 1.4322 0.07414 0.06844 -0.0520 0.2415 1.0000
14.500 1.4430 0.07559 0.06987 -0.0519 0.2339 1.0000
14.750 1.4464 0.07811 0.07238 -0.0523 0.2251 1.0000
15.000 1.4454 0.08132 0.07559 -0.0529 0.2164 1.0000
15.250 1.4511 0.08354 0.07776 -0.0532 0.2072 1.0000
15.500 1.4508 0.08667 0.08087 -0.0538 0.1973 1.0000
15.750 1.4489 0.09011 0.08430 -0.0546 0.1874 1.0000
16.000 1.4467 0.09363 0.08779 -0.0554 0.1772 1.0000
16.250 1.4445 0.09719 0.09131 -0.0563 0.1669 1.0000
16.500 1.4412 0.10093 0.09500 -0.0573 0.1567 1.0000
16.750 1.4360 0.10510 0.09914 -0.0586 0.1468 1.0000
17.000 1.4319 0.10912 0.10314 -0.0598 0.1371 1.0000
17.250 1.4267 0.11337 0.10737 -0.0612 0.1282 1.0000
17.500 1.4222 0.11756 0.11152 -0.0627 0.1198 1.0000
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Polar data table (+)
Polar graphs
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