LWK 79-100 (lwk79100-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: LWK 79-100 (lwk79100-il) Reynolds number: 100,000 Max Cl/Cd: 35.51 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-lwk79100-il-100000-n5.txt Download as CSV file: xf-lwk79100-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: LWK 79-100
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.8119 0.09724 0.09206 0.0066 1.0000 0.0298
-12.250 -0.8396 0.08635 0.08111 -0.0010 1.0000 0.0294
-12.000 -0.8675 0.07681 0.07145 -0.0082 1.0000 0.0292
-11.750 -0.8917 0.06927 0.06374 -0.0137 1.0000 0.0290
-11.500 -0.9135 0.06309 0.05738 -0.0178 1.0000 0.0288
-11.250 -0.9334 0.05800 0.05207 -0.0204 1.0000 0.0288
-11.000 -0.9521 0.05385 0.04765 -0.0210 1.0000 0.0290
-10.750 -0.9661 0.05034 0.04385 -0.0198 1.0000 0.0292
-10.500 -0.9723 0.04681 0.03991 -0.0188 1.0000 0.0296
-10.250 -0.9706 0.04353 0.03632 -0.0178 1.0000 0.0302
-10.000 -0.9606 0.04129 0.03397 -0.0170 1.0000 0.0312
-9.750 -0.9482 0.03956 0.03211 -0.0163 1.0000 0.0328
-9.500 -0.9353 0.03756 0.02985 -0.0154 1.0000 0.0347
-9.250 -0.9206 0.03531 0.02724 -0.0145 1.0000 0.0366
-9.000 -0.9035 0.03318 0.02472 -0.0135 1.0000 0.0381
-8.750 -0.8859 0.03133 0.02284 -0.0128 1.0000 0.0404
-8.500 -0.8664 0.03002 0.02143 -0.0122 1.0000 0.0431
-8.250 -0.8459 0.02852 0.01972 -0.0114 1.0000 0.0459
-8.000 -0.8247 0.02707 0.01805 -0.0105 1.0000 0.0486
-7.750 -0.8046 0.02577 0.01679 -0.0099 1.0000 0.0522
-7.500 -0.7830 0.02465 0.01554 -0.0091 1.0000 0.0562
-7.250 -0.7611 0.02351 0.01426 -0.0083 1.0000 0.0600
-7.000 -0.7402 0.02244 0.01322 -0.0075 1.0000 0.0654
-6.750 -0.7176 0.02154 0.01218 -0.0068 1.0000 0.0718
-6.500 -0.6964 0.02050 0.01121 -0.0060 1.0000 0.0788
-6.250 -0.6741 0.01962 0.01032 -0.0053 1.0000 0.0893
-6.000 -0.6515 0.01877 0.00950 -0.0046 1.0000 0.1034
-5.750 -0.6286 0.01797 0.00875 -0.0040 1.0000 0.1224
-5.500 -0.6058 0.01720 0.00810 -0.0034 1.0000 0.1484
-5.250 -0.5826 0.01649 0.00749 -0.0029 1.0000 0.1803
-5.000 -0.5595 0.01579 0.00696 -0.0023 1.0000 0.2181
-4.750 -0.5366 0.01511 0.00649 -0.0017 1.0000 0.2638
-4.500 -0.5137 0.01449 0.00613 -0.0010 1.0000 0.3168
-4.250 -0.4905 0.01399 0.00583 -0.0003 1.0000 0.3707
-4.000 -0.4670 0.01361 0.00564 0.0006 1.0000 0.4192
-3.750 -0.4432 0.01334 0.00551 0.0014 1.0000 0.4614
-3.500 -0.4192 0.01316 0.00542 0.0023 1.0000 0.4964
-3.250 -0.3950 0.01302 0.00532 0.0032 1.0000 0.5261
-3.000 -0.3709 0.01291 0.00524 0.0040 1.0000 0.5519
-2.750 -0.3475 0.01282 0.00519 0.0049 1.0000 0.5737
-2.500 -0.3107 0.01277 0.00511 0.0030 0.9721 0.5970
-2.250 -0.2708 0.01275 0.00508 0.0007 0.9343 0.6175
-2.000 -0.2313 0.01273 0.00500 -0.0014 0.9004 0.6365
-1.750 -0.1954 0.01272 0.00490 -0.0026 0.8709 0.6537
-1.500 -0.1641 0.01273 0.00482 -0.0029 0.8460 0.6698
-1.250 -0.1356 0.01274 0.00476 -0.0025 0.8247 0.6853
-1.000 -0.1084 0.01275 0.00471 -0.0020 0.8068 0.7001
-0.750 -0.0814 0.01275 0.00468 -0.0014 0.7909 0.7134
-0.500 -0.0543 0.01274 0.00465 -0.0009 0.7765 0.7256
-0.250 -0.0271 0.01273 0.00463 -0.0004 0.7629 0.7377
0.000 0.0000 0.01273 0.00462 0.0000 0.7500 0.7500
0.250 0.0271 0.01273 0.00462 0.0004 0.7377 0.7629
0.500 0.0543 0.01274 0.00465 0.0009 0.7256 0.7765
0.750 0.0814 0.01275 0.00468 0.0014 0.7134 0.7909
1.000 0.1084 0.01275 0.00471 0.0020 0.7001 0.8068
1.250 0.1356 0.01274 0.00476 0.0025 0.6853 0.8248
1.500 0.1641 0.01273 0.00482 0.0029 0.6698 0.8460
1.750 0.1954 0.01272 0.00490 0.0026 0.6538 0.8709
2.000 0.2313 0.01273 0.00500 0.0014 0.6365 0.9004
2.250 0.2708 0.01275 0.00508 -0.0007 0.6175 0.9344
2.500 0.3107 0.01277 0.00511 -0.0030 0.5971 0.9722
2.750 0.3474 0.01282 0.00519 -0.0049 0.5737 1.0000
3.000 0.3708 0.01291 0.00524 -0.0040 0.5519 1.0000
3.250 0.3949 0.01302 0.00532 -0.0032 0.5260 1.0000
3.500 0.4191 0.01316 0.00542 -0.0023 0.4963 1.0000
3.750 0.4431 0.01334 0.00550 -0.0014 0.4613 1.0000
4.000 0.4670 0.01361 0.00564 -0.0006 0.4192 1.0000
4.250 0.4905 0.01399 0.00583 0.0003 0.3708 1.0000
4.500 0.5136 0.01449 0.00613 0.0010 0.3167 1.0000
4.750 0.5365 0.01511 0.00649 0.0017 0.2638 1.0000
5.000 0.5595 0.01579 0.00696 0.0023 0.2181 1.0000
5.250 0.5826 0.01649 0.00749 0.0029 0.1804 1.0000
5.500 0.6058 0.01720 0.00810 0.0034 0.1484 1.0000
5.750 0.6287 0.01797 0.00875 0.0040 0.1224 1.0000
6.000 0.6515 0.01877 0.00950 0.0046 0.1033 1.0000
6.250 0.6741 0.01962 0.01032 0.0053 0.0893 1.0000
6.500 0.6964 0.02050 0.01121 0.0060 0.0788 1.0000
6.750 0.7177 0.02154 0.01219 0.0068 0.0717 1.0000
7.000 0.7403 0.02244 0.01322 0.0075 0.0653 1.0000
7.250 0.7612 0.02352 0.01426 0.0082 0.0600 1.0000
7.500 0.7832 0.02465 0.01554 0.0091 0.0562 1.0000
7.750 0.8048 0.02577 0.01679 0.0098 0.0521 1.0000
8.000 0.8248 0.02708 0.01806 0.0105 0.0486 1.0000
8.250 0.8461 0.02852 0.01973 0.0113 0.0459 1.0000
8.500 0.8666 0.03003 0.02144 0.0121 0.0431 1.0000
8.750 0.8861 0.03134 0.02284 0.0128 0.0403 1.0000
9.000 0.9038 0.03319 0.02473 0.0135 0.0381 1.0000
9.250 0.9208 0.03533 0.02727 0.0144 0.0366 1.0000
9.500 0.9355 0.03757 0.02987 0.0153 0.0347 1.0000
9.750 0.9485 0.03960 0.03216 0.0162 0.0328 1.0000
10.000 0.9609 0.04133 0.03402 0.0170 0.0313 1.0000
10.250 0.9709 0.04355 0.03634 0.0177 0.0302 1.0000
10.500 0.9729 0.04682 0.03991 0.0187 0.0296 1.0000
10.750 0.9663 0.05040 0.04391 0.0197 0.0292 1.0000
11.000 0.9525 0.05387 0.04768 0.0209 0.0290 1.0000
11.250 0.9343 0.05801 0.05207 0.0203 0.0289 1.0000
11.500 0.9145 0.06309 0.05737 0.0177 0.0289 1.0000
11.750 0.8913 0.06948 0.06396 0.0134 0.0289 1.0000
12.000 0.8682 0.07687 0.07151 0.0080 0.0292 1.0000
12.250 0.8400 0.08650 0.08126 0.0007 0.0294 1.0000
12.500 0.8136 0.09706 0.09188 -0.0066 0.0298 1.0000
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