LNV109A (lnv109a-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: LNV109A (lnv109a-il) Reynolds number: 1,000,000 Max Cl/Cd: 151.49 at α=10° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-lnv109a-il-1000000.txt Download as CSV file: xf-lnv109a-il-1000000.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 = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.000 -0.2103 0.08722 0.08358 -0.0007 0.4339 0.0298
-6.750 -0.2030 0.08483 0.08120 -0.0017 0.4331 0.0301
-6.500 -0.1967 0.08244 0.07882 -0.0025 0.4323 0.0305
-6.250 -0.1938 0.08002 0.07642 -0.0033 0.4315 0.0313
-5.750 -0.1955 0.06958 0.06598 -0.0151 0.4305 0.0326
-5.500 -0.1796 0.06748 0.06387 -0.0163 0.4294 0.0327
-5.250 -0.1626 0.06549 0.06187 -0.0176 0.4281 0.0328
-5.000 -0.1448 0.06336 0.05973 -0.0195 0.4265 0.0330
-4.750 -0.1257 0.06099 0.05735 -0.0217 0.4262 0.0333
-4.500 -0.1052 0.05842 0.05477 -0.0243 0.4259 0.0337
-4.250 -0.0735 0.04677 0.04289 -0.0389 0.4257 0.0363
-4.000 -0.0515 0.04507 0.04116 -0.0398 0.4252 0.0365
-3.750 -0.0275 0.04351 0.03958 -0.0407 0.4245 0.0367
-3.500 -0.0022 0.01740 0.01147 -0.0538 0.4246 0.0364
-3.250 0.0254 0.01639 0.01034 -0.0537 0.4238 0.0368
-3.000 0.0538 0.01592 0.00984 -0.0535 0.4229 0.0371
-2.750 0.0824 0.01557 0.00944 -0.0533 0.4220 0.0374
-2.500 0.1110 0.01514 0.00895 -0.0531 0.4211 0.0378
-2.250 0.1396 0.01462 0.00833 -0.0529 0.4201 0.0382
-2.000 0.1683 0.01408 0.00769 -0.0527 0.4191 0.0388
-1.750 0.1970 0.01360 0.00709 -0.0525 0.4181 0.0393
-1.500 0.2260 0.01328 0.00668 -0.0523 0.4170 0.0399
-1.250 0.2551 0.01305 0.00636 -0.0520 0.4159 0.0403
-1.000 0.2835 0.01236 0.00558 -0.0518 0.4150 0.0408
-0.750 0.3122 0.01203 0.00525 -0.0516 0.4140 0.0412
-0.500 0.3411 0.01185 0.00505 -0.0514 0.4129 0.0417
-0.250 0.3700 0.01171 0.00489 -0.0512 0.4116 0.0423
0.000 0.3986 0.01168 0.00484 -0.0510 0.4096 0.0429
0.250 0.4275 0.01157 0.00471 -0.0508 0.4085 0.0436
0.500 0.4566 0.01141 0.00454 -0.0506 0.4079 0.0443
0.750 0.4857 0.01127 0.00440 -0.0504 0.4072 0.0449
1.000 0.5144 0.01097 0.00413 -0.0503 0.4064 0.0458
1.250 0.5434 0.01084 0.00403 -0.0501 0.4055 0.0467
1.500 0.5724 0.01073 0.00394 -0.0499 0.4044 0.0476
1.750 0.6015 0.01063 0.00385 -0.0497 0.4032 0.0486
2.000 0.6306 0.01055 0.00377 -0.0496 0.4020 0.0495
2.250 0.6594 0.01039 0.00363 -0.0494 0.4008 0.0510
2.500 0.6884 0.01033 0.00359 -0.0493 0.3997 0.0526
2.750 0.7175 0.01029 0.00355 -0.0491 0.3986 0.0544
3.000 0.7464 0.01020 0.00347 -0.0490 0.3974 0.0567
3.250 0.7753 0.01017 0.00345 -0.0488 0.3961 0.0594
3.500 0.8041 0.01018 0.00347 -0.0487 0.3945 0.0629
3.750 0.8326 0.01034 0.00363 -0.0486 0.3925 0.0675
4.000 0.8616 0.01026 0.00362 -0.0485 0.3918 0.0770
4.250 0.8904 0.01014 0.00364 -0.0484 0.3908 0.1090
4.500 0.9187 0.00988 0.00373 -0.0483 0.3896 0.2569
4.750 0.9510 0.00845 0.00391 -0.0494 0.3883 1.0000
5.000 0.9799 0.00850 0.00394 -0.0493 0.3869 1.0000
5.250 1.0087 0.00854 0.00396 -0.0492 0.3853 1.0000
5.500 1.0375 0.00858 0.00398 -0.0491 0.3838 1.0000
5.750 1.0662 0.00862 0.00400 -0.0490 0.3823 1.0000
6.000 1.0949 0.00868 0.00404 -0.0489 0.3807 1.0000
6.250 1.1232 0.00881 0.00413 -0.0488 0.3787 1.0000
6.500 1.1516 0.00895 0.00427 -0.0487 0.3768 1.0000
6.750 1.1802 0.00900 0.00434 -0.0486 0.3755 1.0000
7.000 1.2088 0.00905 0.00442 -0.0486 0.3738 1.0000
7.250 1.2373 0.00911 0.00449 -0.0485 0.3719 1.0000
7.500 1.2658 0.00917 0.00456 -0.0484 0.3699 1.0000
7.750 1.2942 0.00923 0.00462 -0.0484 0.3679 1.0000
8.000 1.3224 0.00932 0.00470 -0.0483 0.3657 1.0000
8.250 1.3502 0.00950 0.00485 -0.0482 0.3628 1.0000
8.500 1.3784 0.00957 0.00497 -0.0482 0.3611 1.0000
8.750 1.4067 0.00965 0.00510 -0.0482 0.3587 1.0000
9.000 1.4349 0.00969 0.00516 -0.0482 0.3548 1.0000
9.250 1.4624 0.00980 0.00520 -0.0481 0.3481 1.0000
9.500 1.4906 0.00985 0.00530 -0.0481 0.3414 1.0000
9.750 1.5177 0.01004 0.00546 -0.0480 0.3355 1.0000
10.000 1.5452 0.01020 0.00564 -0.0480 0.3309 1.0000
10.250 1.5724 0.01038 0.00585 -0.0480 0.3254 1.0000
10.500 1.5989 0.01065 0.00610 -0.0479 0.3196 1.0000
10.750 1.6260 0.01085 0.00633 -0.0478 0.3139 1.0000
11.000 1.6517 0.01119 0.00665 -0.0478 0.3064 1.0000
11.250 1.6781 0.01145 0.00693 -0.0477 0.2993 1.0000
11.500 1.7031 0.01187 0.00733 -0.0476 0.2910 1.0000
11.750 1.7279 0.01228 0.00774 -0.0474 0.2813 1.0000
12.000 1.7518 0.01280 0.00824 -0.0473 0.2700 1.0000
12.250 1.7739 0.01348 0.00888 -0.0470 0.2563 1.0000
12.500 1.7944 0.01432 0.00966 -0.0467 0.2414 1.0000
12.750 1.8119 0.01540 0.01067 -0.0462 0.2247 1.0000
13.000 1.8261 0.01670 0.01191 -0.0456 0.2076 1.0000
13.250 1.8345 0.01839 0.01355 -0.0448 0.1890 1.0000
13.500 1.8319 0.02087 0.01601 -0.0438 0.1735 1.0000
13.750 1.7919 0.02835 0.02370 -0.0464 0.1709 1.0000
14.000 1.7529 0.03517 0.03064 -0.0474 0.1674 1.0000
14.250 1.7174 0.04137 0.03690 -0.0480 0.1622 1.0000
14.500 1.6823 0.04747 0.04304 -0.0487 0.1564 1.0000
14.750 1.6575 0.05257 0.04818 -0.0491 0.1498 1.0000
15.000 1.6352 0.05765 0.05325 -0.0497 0.1416 1.0000
15.250 1.6163 0.06251 0.05808 -0.0503 0.1326 1.0000
15.500 1.6009 0.06708 0.06264 -0.0508 0.1241 1.0000
15.750 1.5901 0.07113 0.06668 -0.0513 0.1162 1.0000
16.000 1.5783 0.07541 0.07094 -0.0518 0.1083 1.0000
16.250 1.5672 0.07968 0.07519 -0.0525 0.1014 1.0000
16.500 1.5609 0.08338 0.07887 -0.0530 0.0943 1.0000
16.750 1.5518 0.08760 0.08309 -0.0538 0.0883 1.0000
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Polar data table (+)
Polar graphs
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