LWK 80-120/K25 (lwk80120k25-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: LWK 80-120/K25 (lwk80120k25-il) Reynolds number: 100,000 Max Cl/Cd: 40.74 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-lwk80120k25-il-100000.txt Download as CSV file: xf-lwk80120k25-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: LWK 80-120/K25
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.6062 0.07345 0.06865 -0.0434 1.0000 0.0826
-11.000 -0.6154 0.06771 0.06290 -0.0443 1.0000 0.0812
-10.750 -0.6427 0.06143 0.05656 -0.0456 1.0000 0.0797
-10.500 -0.8358 0.06692 0.06116 -0.0373 1.0000 0.0709
-10.250 -0.8304 0.06213 0.05627 -0.0365 1.0000 0.0690
-10.000 -0.8382 0.05804 0.05201 -0.0343 1.0000 0.0682
-9.750 -0.8453 0.05414 0.04787 -0.0316 1.0000 0.0674
-9.500 -0.8513 0.05056 0.04398 -0.0286 1.0000 0.0674
-9.250 -0.8566 0.04750 0.04049 -0.0250 1.0000 0.0687
-9.000 -0.8573 0.04473 0.03729 -0.0216 1.0000 0.0695
-8.750 -0.8560 0.04236 0.03446 -0.0179 1.0000 0.0703
-8.500 -0.8510 0.03870 0.03054 -0.0151 1.0000 0.0713
-8.250 -0.8420 0.03630 0.02806 -0.0127 1.0000 0.0735
-8.000 -0.8343 0.03512 0.02685 -0.0097 1.0000 0.0769
-7.750 -0.8301 0.03370 0.02515 -0.0059 1.0000 0.0800
-7.500 -0.8246 0.03232 0.02336 -0.0021 1.0000 0.0829
-7.250 -0.8101 0.03010 0.02104 -0.0002 1.0000 0.0867
-7.000 -0.7977 0.02904 0.01991 0.0022 1.0000 0.0925
-6.750 -0.7840 0.02788 0.01842 0.0047 1.0000 0.0979
-6.500 -0.7656 0.02636 0.01703 0.0059 1.0000 0.1052
-6.250 -0.7493 0.02527 0.01579 0.0078 1.0000 0.1134
-6.000 -0.7321 0.02424 0.01481 0.0095 1.0000 0.1223
-5.750 -0.7159 0.02323 0.01385 0.0112 1.0000 0.1334
-5.500 -0.7002 0.02229 0.01296 0.0132 1.0000 0.1459
-5.250 -0.6860 0.02142 0.01218 0.0153 1.0000 0.1620
-5.000 -0.6728 0.02056 0.01144 0.0176 1.0000 0.1829
-4.750 -0.6617 0.01956 0.01068 0.0202 1.0000 0.2145
-4.500 -0.6554 0.01819 0.00995 0.0235 1.0000 0.2817
-4.250 -0.6610 0.01622 0.00944 0.0292 1.0000 0.4888
-4.000 -0.6558 0.01658 0.01069 0.0359 1.0000 0.6886
-3.750 -0.6445 0.01724 0.01128 0.0402 1.0000 0.7425
-3.500 -0.6322 0.01787 0.01182 0.0444 1.0000 0.7763
-3.250 -0.6168 0.01856 0.01243 0.0483 1.0000 0.8022
-3.000 -0.6021 0.01906 0.01282 0.0520 1.0000 0.8254
-2.750 -0.5850 0.01953 0.01321 0.0553 1.0000 0.8473
-2.500 -0.5691 0.01981 0.01339 0.0584 1.0000 0.8680
-2.250 -0.5368 0.02044 0.01388 0.0589 1.0000 0.8869
-2.000 -0.4777 0.02161 0.01489 0.0544 0.9992 0.9078
-1.750 -0.3563 0.02362 0.01664 0.0387 1.0000 0.9295
-1.500 -0.2986 0.02404 0.01692 0.0327 1.0000 0.9427
-1.250 -0.2369 0.02424 0.01701 0.0255 0.9988 0.9510
-1.000 -0.1879 0.02433 0.01701 0.0202 0.9958 0.9587
-0.750 -0.1388 0.02433 0.01695 0.0149 0.9926 0.9650
-0.500 -0.0931 0.02438 0.01695 0.0100 0.9892 0.9709
-0.250 -0.0460 0.02434 0.01689 0.0049 0.9852 0.9760
0.000 -0.0001 0.02440 0.01693 0.0000 0.9809 0.9808
0.250 0.0457 0.02434 0.01689 -0.0048 0.9759 0.9850
0.500 0.0923 0.02438 0.01695 -0.0099 0.9710 0.9891
0.750 0.1389 0.02433 0.01694 -0.0148 0.9650 0.9926
1.000 0.1885 0.02432 0.01700 -0.0203 0.9588 0.9959
1.250 0.2370 0.02423 0.01700 -0.0255 0.9510 0.9988
1.500 0.3002 0.02401 0.01690 -0.0330 0.9426 1.0000
1.750 0.3530 0.02367 0.01668 -0.0382 0.9298 1.0000
2.000 0.4779 0.02161 0.01489 -0.0545 0.9081 0.9993
2.250 0.5375 0.02041 0.01386 -0.0589 0.8867 1.0000
2.500 0.5695 0.01979 0.01336 -0.0584 0.8677 1.0000
2.750 0.5850 0.01953 0.01320 -0.0553 0.8472 1.0000
3.000 0.6020 0.01905 0.01281 -0.0520 0.8253 1.0000
3.250 0.6167 0.01856 0.01243 -0.0482 0.8022 1.0000
3.500 0.6322 0.01786 0.01180 -0.0444 0.7761 1.0000
3.750 0.6443 0.01724 0.01128 -0.0402 0.7423 1.0000
4.000 0.6556 0.01656 0.01067 -0.0358 0.6881 1.0000
4.250 0.6608 0.01622 0.00944 -0.0292 0.4873 1.0000
4.500 0.6550 0.01821 0.00995 -0.0234 0.2800 1.0000
4.750 0.6616 0.01956 0.01070 -0.0202 0.2143 1.0000
5.000 0.6727 0.02055 0.01143 -0.0176 0.1830 1.0000
5.250 0.6859 0.02140 0.01217 -0.0153 0.1621 1.0000
5.500 0.7001 0.02229 0.01295 -0.0131 0.1458 1.0000
5.750 0.7158 0.02324 0.01385 -0.0112 0.1333 1.0000
6.000 0.7317 0.02421 0.01478 -0.0094 0.1218 1.0000
6.250 0.7493 0.02528 0.01580 -0.0078 0.1134 1.0000
6.500 0.7659 0.02640 0.01707 -0.0059 0.1053 1.0000
6.750 0.7840 0.02791 0.01845 -0.0047 0.0978 1.0000
7.000 0.7972 0.02900 0.01987 -0.0021 0.0922 1.0000
7.250 0.8099 0.03006 0.02100 0.0002 0.0868 1.0000
7.500 0.8243 0.03230 0.02334 0.0021 0.0829 1.0000
7.750 0.8303 0.03374 0.02519 0.0059 0.0803 1.0000
8.000 0.8341 0.03510 0.02683 0.0098 0.0768 1.0000
8.250 0.8419 0.03636 0.02812 0.0127 0.0734 1.0000
8.500 0.8509 0.03874 0.03058 0.0151 0.0713 1.0000
8.750 0.8550 0.04223 0.03436 0.0181 0.0701 1.0000
9.000 0.8564 0.04461 0.03720 0.0218 0.0693 1.0000
9.250 0.8543 0.04734 0.04039 0.0254 0.0679 1.0000
9.500 0.8520 0.05063 0.04403 0.0285 0.0676 1.0000
9.750 0.8449 0.05419 0.04793 0.0317 0.0673 1.0000
10.000 0.8366 0.05808 0.05207 0.0344 0.0680 1.0000
10.250 0.8270 0.06222 0.05639 0.0368 0.0688 1.0000
10.500 0.8359 0.06723 0.06147 0.0372 0.0708 1.0000
10.750 0.6389 0.06134 0.05647 0.0455 0.0790 1.0000
11.000 0.6153 0.06758 0.06277 0.0443 0.0813 1.0000
11.250 0.6005 0.07363 0.06884 0.0429 0.0825 1.0000
|
Polar data table (+)
Polar graphs
<< Back to LWK 80-120/K25 (lwk80120k25-il)