LWK 80-120/K25 (lwk80120k25-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: LWK 80-120/K25 (lwk80120k25-il) Reynolds number: 50,000 Max Cl/Cd: 27.19 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-lwk80120k25-il-50000-n5.txt Download as CSV file: xf-lwk80120k25-il-50000-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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.6676 0.09988 0.09246 -0.0295 1.0000 0.0568
-12.000 -0.6876 0.09173 0.08430 -0.0346 1.0000 0.0564
-11.750 -0.7102 0.08451 0.07705 -0.0387 1.0000 0.0559
-11.500 -0.7344 0.07829 0.07077 -0.0415 1.0000 0.0554
-11.250 -0.7593 0.07296 0.06532 -0.0428 1.0000 0.0552
-11.000 -0.7813 0.06848 0.06069 -0.0428 1.0000 0.0549
-10.750 -0.8046 0.06462 0.05661 -0.0413 1.0000 0.0555
-10.500 -0.8225 0.06127 0.05305 -0.0387 1.0000 0.0558
-10.250 -0.8382 0.05798 0.04943 -0.0358 1.0000 0.0566
-10.000 -0.8481 0.05468 0.04571 -0.0329 1.0000 0.0574
-9.750 -0.8482 0.05156 0.04232 -0.0306 1.0000 0.0587
-9.500 -0.8400 0.04899 0.03958 -0.0291 1.0000 0.0603
-9.250 -0.8313 0.04678 0.03720 -0.0273 1.0000 0.0628
-9.000 -0.8226 0.04455 0.03466 -0.0254 1.0000 0.0662
-8.750 -0.8135 0.04209 0.03168 -0.0231 1.0000 0.0697
-8.500 -0.7961 0.03984 0.02934 -0.0220 1.0000 0.0729
-8.250 -0.7804 0.03823 0.02762 -0.0206 1.0000 0.0777
-8.000 -0.7633 0.03650 0.02542 -0.0190 1.0000 0.0835
-7.750 -0.7418 0.03484 0.02387 -0.0183 1.0000 0.0889
-7.500 -0.7223 0.03353 0.02227 -0.0169 1.0000 0.0969
-7.250 -0.7015 0.03224 0.02109 -0.0160 1.0000 0.1046
-7.000 -0.6800 0.03110 0.01985 -0.0148 1.0000 0.1143
-6.750 -0.6619 0.03017 0.01881 -0.0132 1.0000 0.1257
-6.500 -0.6475 0.02923 0.01792 -0.0111 1.0000 0.1365
-6.250 -0.6378 0.02842 0.01715 -0.0084 1.0000 0.1495
-6.000 -0.6303 0.02762 0.01640 -0.0053 1.0000 0.1640
-5.750 -0.6243 0.02682 0.01566 -0.0019 1.0000 0.1816
-5.500 -0.6201 0.02595 0.01496 0.0016 1.0000 0.2054
-5.250 -0.6170 0.02500 0.01424 0.0052 1.0000 0.2387
-5.000 -0.6154 0.02392 0.01350 0.0090 1.0000 0.2919
-4.750 -0.6155 0.02271 0.01291 0.0133 1.0000 0.3790
-4.500 -0.6051 0.02227 0.01363 0.0181 1.0000 0.5426
-4.250 -0.5874 0.02303 0.01458 0.0221 1.0000 0.6476
-4.000 -0.5812 0.02330 0.01471 0.0266 1.0000 0.6984
-3.750 -0.5669 0.02380 0.01504 0.0301 0.9988 0.7365
-3.500 -0.5409 0.02451 0.01553 0.0317 0.9942 0.7714
-3.250 -0.5105 0.02531 0.01614 0.0328 0.9906 0.8019
-3.000 -0.4721 0.02620 0.01680 0.0327 0.9885 0.8308
-2.750 -0.4316 0.02681 0.01721 0.0316 0.9863 0.8550
-2.500 -0.3845 0.02721 0.01739 0.0286 0.9846 0.8722
-2.250 -0.3430 0.02733 0.01728 0.0259 0.9819 0.8853
-2.000 -0.3066 0.02732 0.01711 0.0237 0.9785 0.8968
-1.750 -0.2587 0.02730 0.01693 0.0193 0.9760 0.9036
-1.500 -0.2260 0.02722 0.01671 0.0174 0.9717 0.9127
-1.250 -0.1790 0.02718 0.01656 0.0129 0.9691 0.9179
-1.000 -0.1487 0.02709 0.01638 0.0114 0.9642 0.9255
-0.750 -0.1090 0.02703 0.01626 0.0081 0.9602 0.9307
-0.500 -0.0683 0.02700 0.01619 0.0046 0.9567 0.9359
-0.250 -0.0403 0.02697 0.01612 0.0035 0.9510 0.9425
0.000 0.0001 0.02695 0.01609 0.0000 0.9465 0.9465
0.250 0.0406 0.02697 0.01612 -0.0035 0.9424 0.9510
0.500 0.0682 0.02700 0.01618 -0.0045 0.9359 0.9567
0.750 0.1088 0.02703 0.01626 -0.0081 0.9308 0.9602
1.000 0.1487 0.02709 0.01638 -0.0114 0.9256 0.9642
1.250 0.1790 0.02718 0.01656 -0.0129 0.9179 0.9691
1.750 0.2586 0.02730 0.01693 -0.0193 0.9036 0.9760
2.000 0.3069 0.02731 0.01710 -0.0237 0.8969 0.9785
2.250 0.3436 0.02731 0.01727 -0.0260 0.8852 0.9818
2.500 0.3848 0.02720 0.01735 -0.0287 0.8721 0.9845
2.750 0.4312 0.02682 0.01722 -0.0315 0.8552 0.9864
3.000 0.4722 0.02619 0.01680 -0.0327 0.8307 0.9885
3.250 0.5106 0.02531 0.01613 -0.0328 0.8020 0.9906
3.500 0.5411 0.02450 0.01553 -0.0317 0.7713 0.9943
3.750 0.5669 0.02378 0.01502 -0.0300 0.7360 0.9989
4.000 0.5809 0.02330 0.01470 -0.0266 0.6980 1.0000
4.250 0.5873 0.02302 0.01458 -0.0221 0.6478 1.0000
4.500 0.6052 0.02226 0.01361 -0.0181 0.5416 1.0000
4.750 0.6155 0.02270 0.01291 -0.0133 0.3797 1.0000
5.000 0.6153 0.02392 0.01350 -0.0090 0.2918 1.0000
5.250 0.6170 0.02499 0.01423 -0.0052 0.2391 1.0000
5.500 0.6200 0.02595 0.01495 -0.0016 0.2052 1.0000
5.750 0.6242 0.02681 0.01565 0.0019 0.1815 1.0000
6.000 0.6302 0.02762 0.01639 0.0053 0.1637 1.0000
6.250 0.6378 0.02842 0.01714 0.0084 0.1496 1.0000
6.500 0.6476 0.02923 0.01792 0.0112 0.1363 1.0000
6.750 0.6618 0.03017 0.01881 0.0133 0.1255 1.0000
7.000 0.6798 0.03110 0.01984 0.0149 0.1142 1.0000
7.250 0.7016 0.03224 0.02109 0.0160 0.1047 1.0000
7.500 0.7219 0.03351 0.02227 0.0170 0.0968 1.0000
7.750 0.7414 0.03482 0.02384 0.0183 0.0888 1.0000
8.000 0.7637 0.03652 0.02547 0.0190 0.0835 1.0000
8.250 0.7804 0.03825 0.02763 0.0206 0.0776 1.0000
8.500 0.7964 0.03987 0.02937 0.0220 0.0729 1.0000
8.750 0.8133 0.04213 0.03173 0.0231 0.0696 1.0000
9.000 0.8227 0.04457 0.03469 0.0254 0.0661 1.0000
9.250 0.8313 0.04670 0.03709 0.0273 0.0624 1.0000
9.500 0.8401 0.04901 0.03960 0.0291 0.0603 1.0000
9.750 0.8484 0.05161 0.04236 0.0306 0.0586 1.0000
10.000 0.8481 0.05475 0.04579 0.0328 0.0575 1.0000
10.250 0.8369 0.05810 0.04957 0.0358 0.0565 1.0000
10.500 0.8229 0.06138 0.05315 0.0387 0.0559 1.0000
10.750 0.8029 0.06474 0.05674 0.0413 0.0553 1.0000
11.000 0.7819 0.06858 0.06078 0.0427 0.0551 1.0000
11.250 0.7586 0.07311 0.06547 0.0427 0.0551 1.0000
11.500 0.7344 0.07840 0.07089 0.0413 0.0554 1.0000
11.750 0.7134 0.08432 0.07685 0.0388 0.0561 1.0000
12.000 0.6876 0.09196 0.08453 0.0343 0.0564 1.0000
12.250 0.6679 0.10011 0.09268 0.0293 0.0568 1.0000
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