LWK 80-080 (lwk80080-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: LWK 80-080 (lwk80080-il) Reynolds number: 200,000 Max Cl/Cd: 45.92 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-lwk80080-il-200000.txt Download as CSV file: xf-lwk80080-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: LWK 80-080
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
------ -------- --------- --------- -------- -------- --------
-12.000 -0.4813 0.11992 0.11657 -0.0008 1.0000 0.0426
-11.750 -0.4903 0.11680 0.11346 -0.0035 1.0000 0.0437
-11.500 -0.4979 0.11317 0.10985 -0.0063 1.0000 0.0442
-11.250 -0.5038 0.10908 0.10577 -0.0088 1.0000 0.0444
-11.000 -0.5087 0.10471 0.10142 -0.0111 1.0000 0.0446
-10.750 -0.5138 0.10001 0.09673 -0.0135 1.0000 0.0447
-10.500 -0.5198 0.09502 0.09175 -0.0161 1.0000 0.0447
-10.250 -0.5108 0.08993 0.08669 -0.0122 1.0000 0.0469
-10.000 -0.5097 0.08608 0.08284 -0.0126 1.0000 0.0479
-9.750 -0.5125 0.08170 0.07848 -0.0138 1.0000 0.0488
-9.500 -0.5173 0.07701 0.07381 -0.0152 1.0000 0.0504
-9.250 -0.5262 0.07161 0.06844 -0.0175 1.0000 0.0509
-9.000 -0.5387 0.06574 0.06260 -0.0207 1.0000 0.0513
-8.750 -0.5602 0.05899 0.05585 -0.0257 1.0000 0.0508
-8.500 -0.5842 0.05375 0.05057 -0.0281 1.0000 0.0505
-8.250 -0.7064 0.06402 0.06025 -0.0236 1.0000 0.0464
-8.000 -0.7010 0.06064 0.05685 -0.0229 1.0000 0.0475
-7.750 -0.6966 0.05735 0.05348 -0.0220 1.0000 0.0491
-7.500 -0.6919 0.05401 0.05000 -0.0210 1.0000 0.0510
-7.250 -0.6868 0.05055 0.04629 -0.0197 1.0000 0.0539
-7.000 -0.6896 0.04625 0.04141 -0.0170 1.0000 0.0592
-6.750 -0.6763 0.04287 0.03807 -0.0160 1.0000 0.0615
-6.500 -0.6659 0.03330 0.02736 -0.0105 1.0000 0.0311
-6.250 -0.6537 0.02946 0.02311 -0.0081 1.0000 0.0301
-6.000 -0.6366 0.02814 0.02131 -0.0058 1.0000 0.0330
-5.750 -0.6171 0.02607 0.01892 -0.0040 1.0000 0.0324
-5.500 -0.5986 0.02294 0.01545 -0.0021 1.0000 0.0321
-5.250 -0.5785 0.02094 0.01320 -0.0004 1.0000 0.0323
-5.000 -0.5591 0.01871 0.01078 0.0014 1.0000 0.0332
-4.750 -0.5436 0.01695 0.00904 0.0037 1.0000 0.0377
-4.500 -0.5292 0.01609 0.00812 0.0062 1.0000 0.0416
-4.250 -0.5168 0.01519 0.00718 0.0090 1.0000 0.0469
-4.000 -0.5030 0.01460 0.00657 0.0115 1.0000 0.0589
-3.750 -0.4898 0.01388 0.00591 0.0139 1.0000 0.0735
-3.500 -0.4756 0.01320 0.00525 0.0162 1.0000 0.0937
-3.250 -0.4629 0.01234 0.00471 0.0187 1.0000 0.1495
-3.000 -0.4576 0.01043 0.00425 0.0218 0.9984 0.4381
-2.750 -0.4409 0.00960 0.00462 0.0245 0.9927 0.7230
-2.500 -0.4125 0.00977 0.00485 0.0250 0.9882 0.7919
-2.250 -0.3836 0.00993 0.00499 0.0254 0.9835 0.8318
-2.000 -0.3521 0.01007 0.00507 0.0252 0.9799 0.8604
-1.750 -0.3232 0.01014 0.00510 0.0254 0.9753 0.8819
-1.500 -0.2891 0.01025 0.00517 0.0246 0.9721 0.9038
-1.250 -0.2490 0.01046 0.00535 0.0229 0.9706 0.9287
-1.000 -0.1938 0.01081 0.00562 0.0180 0.9718 0.9461
-0.750 -0.1433 0.01101 0.00574 0.0134 0.9713 0.9555
-0.500 -0.0911 0.01111 0.00581 0.0081 0.9708 0.9586
-0.250 -0.0427 0.01116 0.00582 0.0035 0.9693 0.9617
0.000 -0.0001 0.01118 0.00582 0.0000 0.9660 0.9660
0.250 0.0425 0.01116 0.00581 -0.0035 0.9617 0.9693
0.500 0.0912 0.01111 0.00580 -0.0081 0.9586 0.9708
0.750 0.1445 0.01100 0.00574 -0.0136 0.9553 0.9711
1.000 0.1941 0.01081 0.00561 -0.0181 0.9460 0.9718
1.250 0.2506 0.01043 0.00532 -0.0231 0.9274 0.9702
1.500 0.2892 0.01023 0.00514 -0.0245 0.9018 0.9718
1.750 0.3233 0.01014 0.00511 -0.0254 0.8823 0.9753
2.000 0.3521 0.01008 0.00509 -0.0252 0.8612 0.9800
2.250 0.3837 0.00994 0.00502 -0.0255 0.8338 0.9835
2.500 0.4120 0.00976 0.00481 -0.0248 0.7887 0.9882
2.750 0.4408 0.00960 0.00461 -0.0245 0.7221 0.9927
3.000 0.4577 0.01045 0.00425 -0.0219 0.4347 0.9985
3.250 0.4632 0.01230 0.00470 -0.0187 0.1535 1.0000
3.500 0.4755 0.01322 0.00527 -0.0162 0.0952 1.0000
3.750 0.4890 0.01398 0.00597 -0.0138 0.0713 1.0000
4.000 0.5035 0.01452 0.00651 -0.0116 0.0545 1.0000
4.250 0.5149 0.01550 0.00743 -0.0088 0.0446 1.0000
4.500 0.5293 0.01606 0.00811 -0.0062 0.0393 1.0000
4.750 0.5429 0.01699 0.00902 -0.0036 0.0349 1.0000
5.000 0.5589 0.01940 0.01150 -0.0013 0.0325 1.0000
5.250 0.5785 0.02089 0.01317 0.0005 0.0320 1.0000
5.500 0.5986 0.02283 0.01537 0.0023 0.0316 1.0000
5.750 0.6171 0.02599 0.01886 0.0041 0.0323 1.0000
6.000 0.6362 0.02842 0.02162 0.0059 0.0330 1.0000
6.500 0.6683 0.03428 0.02861 0.0116 0.0366 1.0000
14.500 0.6834 0.17819 0.17440 -0.0332 0.0255 1.0000
14.750 0.6896 0.18190 0.17811 -0.0345 0.0243 1.0000
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Polar data table (+)
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