LWK 80-120/K25 (lwk80120k25-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: LWK 80-120/K25 (lwk80120k25-il) Reynolds number: 100,000 Max Cl/Cd: 30.07 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-lwk80120k25-il-100000-n5.txt Download as CSV file: xf-lwk80120k25-il-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.7469 0.08967 0.08429 -0.0321 1.0000 0.0290
-13.000 -0.7711 0.08125 0.07578 -0.0377 1.0000 0.0287
-12.750 -0.7952 0.07422 0.06861 -0.0419 1.0000 0.0284
-12.500 -0.8247 0.06755 0.06174 -0.0447 1.0000 0.0284
-12.250 -0.8453 0.06273 0.05673 -0.0456 1.0000 0.0284
-12.000 -0.8671 0.05824 0.05198 -0.0454 1.0000 0.0285
-11.750 -0.8844 0.05445 0.04792 -0.0442 1.0000 0.0286
-11.500 -0.8997 0.05101 0.04417 -0.0423 1.0000 0.0287
-11.250 -0.9124 0.04795 0.04075 -0.0395 1.0000 0.0291
-11.000 -0.9155 0.04535 0.03796 -0.0371 1.0000 0.0295
-10.750 -0.9135 0.04346 0.03599 -0.0348 1.0000 0.0303
-10.500 -0.9096 0.04167 0.03404 -0.0326 1.0000 0.0310
-10.250 -0.9028 0.04017 0.03239 -0.0306 1.0000 0.0324
-10.000 -0.8949 0.03846 0.03043 -0.0285 1.0000 0.0341
-9.750 -0.8846 0.03640 0.02803 -0.0266 1.0000 0.0358
-9.500 -0.8709 0.03435 0.02565 -0.0249 1.0000 0.0373
-9.250 -0.8559 0.03278 0.02407 -0.0237 1.0000 0.0391
-9.000 -0.8412 0.03167 0.02287 -0.0222 1.0000 0.0413
-8.750 -0.8256 0.03048 0.02150 -0.0206 1.0000 0.0444
-8.500 -0.8081 0.02912 0.01992 -0.0192 1.0000 0.0471
-8.250 -0.7941 0.02797 0.01882 -0.0174 1.0000 0.0497
-8.000 -0.7822 0.02717 0.01799 -0.0152 1.0000 0.0529
-7.750 -0.7719 0.02646 0.01713 -0.0124 1.0000 0.0568
-7.500 -0.7663 0.02566 0.01630 -0.0090 1.0000 0.0598
-7.250 -0.7437 0.02475 0.01537 -0.0090 0.9922 0.0650
-7.000 -0.7152 0.02378 0.01430 -0.0099 0.9854 0.0720
-6.750 -0.6863 0.02288 0.01337 -0.0110 0.9800 0.0798
-6.500 -0.6599 0.02202 0.01250 -0.0115 0.9735 0.0887
-6.000 -0.6038 0.02049 0.01092 -0.0130 0.9630 0.1133
-5.750 -0.5752 0.01972 0.01022 -0.0140 0.9584 0.1313
-5.500 -0.5486 0.01901 0.00958 -0.0145 0.9536 0.1575
-5.250 -0.5254 0.01828 0.00905 -0.0143 0.9481 0.1963
-5.000 -0.5013 0.01739 0.00853 -0.0145 0.9435 0.2642
-4.750 -0.4848 0.01648 0.00810 -0.0131 0.9374 0.3589
-4.500 -0.4697 0.01562 0.00793 -0.0110 0.9316 0.4862
-4.250 -0.4425 0.01562 0.00849 -0.0099 0.9287 0.6081
-4.000 -0.4169 0.01592 0.00881 -0.0087 0.9245 0.6636
-3.750 -0.3942 0.01616 0.00896 -0.0074 0.9193 0.6959
-3.500 -0.3667 0.01644 0.00914 -0.0068 0.9155 0.7210
-3.250 -0.3382 0.01674 0.00933 -0.0065 0.9125 0.7423
-3.000 -0.3193 0.01705 0.00956 -0.0044 0.9071 0.7608
-2.750 -0.2919 0.01747 0.00991 -0.0035 0.9033 0.7774
-2.500 -0.2629 0.01781 0.01019 -0.0030 0.9001 0.7924
-2.250 -0.2300 0.01810 0.01041 -0.0033 0.8978 0.8037
-2.000 -0.2044 0.01830 0.01054 -0.0026 0.8936 0.8125
-1.750 -0.1848 0.01833 0.01052 -0.0011 0.8885 0.8226
-1.500 -0.1511 0.01844 0.01058 -0.0020 0.8857 0.8278
-1.250 -0.1242 0.01841 0.01048 -0.0020 0.8826 0.8351
-1.000 -0.1018 0.01846 0.01051 -0.0011 0.8775 0.8405
-0.750 -0.0754 0.01849 0.01051 -0.0009 0.8733 0.8456
-0.500 -0.0537 0.01841 0.01039 0.0000 0.8692 0.8524
-0.250 -0.0215 0.01844 0.01041 -0.0009 0.8661 0.8555
0.000 0.0000 0.01849 0.01047 0.0000 0.8602 0.8602
0.250 0.0215 0.01844 0.01041 0.0009 0.8555 0.8661
0.500 0.0536 0.01841 0.01039 0.0001 0.8524 0.8692
0.750 0.0754 0.01849 0.01051 0.0009 0.8457 0.8733
1.000 0.1018 0.01846 0.01051 0.0011 0.8405 0.8775
1.250 0.1243 0.01841 0.01048 0.0020 0.8352 0.8826
1.500 0.1511 0.01844 0.01058 0.0020 0.8278 0.8858
1.750 0.1849 0.01833 0.01051 0.0011 0.8226 0.8885
2.000 0.2045 0.01829 0.01055 0.0026 0.8124 0.8936
2.250 0.2300 0.01810 0.01041 0.0034 0.8036 0.8979
2.500 0.2627 0.01783 0.01020 0.0030 0.7926 0.9001
2.750 0.2919 0.01747 0.00991 0.0035 0.7775 0.9033
3.000 0.3193 0.01705 0.00956 0.0044 0.7609 0.9071
3.250 0.3384 0.01674 0.00933 0.0065 0.7427 0.9125
3.500 0.3668 0.01643 0.00913 0.0069 0.7207 0.9155
3.750 0.3941 0.01615 0.00896 0.0074 0.6954 0.9193
4.000 0.4169 0.01591 0.00881 0.0087 0.6635 0.9246
4.250 0.4425 0.01562 0.00848 0.0098 0.6078 0.9287
4.500 0.4695 0.01563 0.00790 0.0111 0.4834 0.9316
4.750 0.4846 0.01649 0.00810 0.0132 0.3581 0.9374
5.000 0.5014 0.01740 0.00853 0.0145 0.2640 0.9436
5.250 0.5255 0.01827 0.00905 0.0143 0.1967 0.9481
5.500 0.5487 0.01901 0.00958 0.0145 0.1574 0.9536
5.750 0.5754 0.01972 0.01022 0.0139 0.1311 0.9585
6.000 0.6040 0.02050 0.01092 0.0130 0.1131 0.9631
6.250 0.6304 0.02122 0.01163 0.0126 0.0995 0.9691
6.500 0.6601 0.02202 0.01250 0.0114 0.0884 0.9736
6.750 0.6865 0.02287 0.01336 0.0109 0.0795 0.9800
7.000 0.7153 0.02379 0.01430 0.0098 0.0719 0.9855
7.250 0.7438 0.02477 0.01540 0.0090 0.0653 0.9923
7.500 0.7662 0.02567 0.01631 0.0090 0.0598 1.0000
7.750 0.7719 0.02645 0.01712 0.0124 0.0568 1.0000
8.000 0.7823 0.02718 0.01800 0.0152 0.0530 1.0000
8.250 0.7939 0.02795 0.01879 0.0175 0.0495 1.0000
8.500 0.8082 0.02914 0.01994 0.0192 0.0471 1.0000
8.750 0.8258 0.03052 0.02153 0.0206 0.0444 1.0000
9.000 0.8414 0.03168 0.02288 0.0222 0.0413 1.0000
9.250 0.8558 0.03276 0.02404 0.0237 0.0389 1.0000
9.500 0.8712 0.03436 0.02567 0.0249 0.0374 1.0000
9.750 0.8847 0.03640 0.02804 0.0266 0.0357 1.0000
10.000 0.8948 0.03827 0.03024 0.0285 0.0337 1.0000
10.250 0.9029 0.03991 0.03210 0.0306 0.0319 1.0000
10.500 0.9099 0.04159 0.03394 0.0325 0.0309 1.0000
10.750 0.9142 0.04332 0.03581 0.0347 0.0300 1.0000
11.000 0.9156 0.04541 0.03802 0.0371 0.0295 1.0000
11.250 0.9114 0.04803 0.04086 0.0396 0.0290 1.0000
11.500 0.8992 0.05112 0.04430 0.0422 0.0287 1.0000
11.750 0.8861 0.05439 0.04784 0.0441 0.0286 1.0000
12.000 0.8653 0.05849 0.05225 0.0453 0.0284 1.0000
12.250 0.8443 0.06294 0.05694 0.0455 0.0283 1.0000
12.500 0.8217 0.06805 0.06227 0.0444 0.0284 1.0000
12.750 0.7927 0.07474 0.06914 0.0414 0.0284 1.0000
13.000 0.7644 0.08271 0.07726 0.0365 0.0286 1.0000
13.250 0.7381 0.09201 0.08666 0.0301 0.0289 1.0000
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