LWK 80-100 (lwk80100-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: LWK 80-100 (lwk80100-il) Reynolds number: 100,000 Max Cl/Cd: 31.93 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-lwk80100-il-100000-n5.txt Download as CSV file: xf-lwk80100-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: LWK 80-100
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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.7186 0.07712 0.07195 -0.0304 1.0000 0.0219
-11.000 -0.7397 0.07066 0.06538 -0.0342 1.0000 0.0218
-10.750 -0.7620 0.06529 0.05986 -0.0362 1.0000 0.0218
-10.500 -0.7845 0.06080 0.05521 -0.0364 1.0000 0.0221
-10.250 -0.8003 0.05738 0.05165 -0.0350 1.0000 0.0223
-9.750 -0.8200 0.05167 0.04561 -0.0304 1.0000 0.0229
-9.500 -0.8205 0.04936 0.04313 -0.0285 1.0000 0.0236
-9.250 -0.8199 0.04677 0.04032 -0.0264 1.0000 0.0242
-9.000 -0.8167 0.04415 0.03743 -0.0243 1.0000 0.0252
-8.750 -0.8135 0.04086 0.03369 -0.0219 1.0000 0.0258
-8.500 -0.8059 0.03789 0.03032 -0.0197 1.0000 0.0265
-8.250 -0.7947 0.03509 0.02710 -0.0176 1.0000 0.0273
-8.000 -0.7802 0.03253 0.02413 -0.0158 1.0000 0.0286
-7.750 -0.7628 0.03048 0.02165 -0.0142 1.0000 0.0303
-7.500 -0.7463 0.02877 0.01990 -0.0129 1.0000 0.0327
-7.250 -0.7285 0.02757 0.01859 -0.0116 1.0000 0.0355
-7.000 -0.7092 0.02607 0.01689 -0.0101 1.0000 0.0384
-6.750 -0.6908 0.02474 0.01539 -0.0085 1.0000 0.0422
-6.500 -0.6751 0.02379 0.01443 -0.0068 1.0000 0.0462
-6.250 -0.6594 0.02281 0.01335 -0.0048 1.0000 0.0506
-6.000 -0.6467 0.02191 0.01241 -0.0024 1.0000 0.0553
-5.750 -0.6354 0.02127 0.01176 0.0003 1.0000 0.0615
-5.500 -0.6246 0.02058 0.01096 0.0032 1.0000 0.0668
-5.250 -0.6014 0.01976 0.01014 0.0033 0.9946 0.0766
-5.000 -0.5729 0.01893 0.00927 0.0025 0.9885 0.0902
-4.750 -0.5444 0.01816 0.00852 0.0018 0.9825 0.1084
-4.500 -0.5172 0.01737 0.00790 0.0012 0.9765 0.1395
-4.250 -0.4902 0.01648 0.00732 0.0006 0.9712 0.1999
-4.000 -0.4686 0.01534 0.00679 0.0008 0.9653 0.3226
-3.750 -0.4509 0.01411 0.00656 0.0023 0.9594 0.5144
-3.500 -0.4229 0.01406 0.00708 0.0034 0.9563 0.6663
-3.250 -0.3980 0.01425 0.00724 0.0046 0.9505 0.7177
-3.000 -0.3694 0.01446 0.00731 0.0049 0.9461 0.7522
-2.750 -0.3382 0.01472 0.00748 0.0048 0.9428 0.7796
-2.500 -0.3121 0.01501 0.00771 0.0059 0.9379 0.8033
-2.250 -0.2863 0.01528 0.00791 0.0071 0.9333 0.8266
-2.000 -0.2533 0.01552 0.00807 0.0069 0.9304 0.8435
-1.750 -0.2196 0.01562 0.00808 0.0060 0.9277 0.8562
-1.500 -0.1889 0.01571 0.00810 0.0056 0.9232 0.8643
-1.250 -0.1596 0.01570 0.00803 0.0052 0.9188 0.8724
-1.000 -0.1234 0.01571 0.00796 0.0035 0.9157 0.8777
-0.750 -0.0958 0.01567 0.00787 0.0032 0.9113 0.8848
-0.500 -0.0633 0.01569 0.00786 0.0021 0.9068 0.8889
-0.250 -0.0308 0.01568 0.00783 0.0009 0.9028 0.8936
0.000 0.0000 0.01564 0.00777 0.0000 0.8991 0.8991
0.250 0.0309 0.01568 0.00783 -0.0009 0.8936 0.9028
0.500 0.0634 0.01569 0.00786 -0.0021 0.8888 0.9068
0.750 0.0960 0.01567 0.00787 -0.0032 0.8848 0.9114
1.000 0.1236 0.01571 0.00796 -0.0035 0.8777 0.9158
1.250 0.1597 0.01570 0.00801 -0.0052 0.8724 0.9188
1.500 0.1891 0.01571 0.00810 -0.0056 0.8644 0.9233
1.750 0.2199 0.01562 0.00808 -0.0060 0.8562 0.9277
2.000 0.2535 0.01551 0.00805 -0.0068 0.8432 0.9304
2.250 0.2861 0.01527 0.00791 -0.0070 0.8262 0.9334
2.500 0.3124 0.01499 0.00769 -0.0059 0.8027 0.9379
2.750 0.3381 0.01471 0.00747 -0.0047 0.7786 0.9428
3.000 0.3692 0.01445 0.00730 -0.0048 0.7511 0.9462
3.250 0.3982 0.01426 0.00724 -0.0046 0.7181 0.9505
3.500 0.4232 0.01406 0.00708 -0.0035 0.6675 0.9562
3.750 0.4509 0.01412 0.00655 -0.0023 0.5124 0.9594
4.000 0.4692 0.01530 0.00681 -0.0009 0.3275 0.9652
4.250 0.4907 0.01643 0.00732 -0.0006 0.2058 0.9712
4.500 0.5176 0.01733 0.00789 -0.0013 0.1423 0.9765
4.750 0.5448 0.01811 0.00851 -0.0018 0.1100 0.9825
5.000 0.5730 0.01891 0.00925 -0.0025 0.0918 0.9885
5.250 0.6018 0.01971 0.01010 -0.0034 0.0770 0.9946
5.500 0.6249 0.02055 0.01095 -0.0032 0.0670 1.0000
5.750 0.6356 0.02125 0.01175 -0.0003 0.0611 1.0000
6.000 0.6469 0.02187 0.01237 0.0023 0.0550 1.0000
6.250 0.6595 0.02280 0.01336 0.0048 0.0503 1.0000
6.500 0.6750 0.02369 0.01433 0.0068 0.0452 1.0000
6.750 0.6900 0.02478 0.01535 0.0086 0.0408 1.0000
7.000 0.7092 0.02607 0.01691 0.0102 0.0376 1.0000
7.250 0.7282 0.02750 0.01852 0.0116 0.0349 1.0000
7.500 0.7451 0.02852 0.01956 0.0129 0.0317 1.0000
7.750 0.7627 0.03039 0.02163 0.0143 0.0295 1.0000
8.000 0.7800 0.03262 0.02425 0.0159 0.0279 1.0000
8.250 0.7944 0.03515 0.02718 0.0177 0.0267 1.0000
8.500 0.8054 0.03791 0.03035 0.0198 0.0258 1.0000
8.750 0.8133 0.04084 0.03371 0.0219 0.0253 1.0000
9.000 0.8177 0.04390 0.03713 0.0242 0.0248 1.0000
9.250 0.8205 0.04665 0.04017 0.0264 0.0241 1.0000
9.500 0.8254 0.04843 0.04206 0.0280 0.0230 1.0000
9.750 0.8227 0.05125 0.04510 0.0302 0.0226 1.0000
10.250 0.7973 0.05766 0.05186 0.0351 0.0219 1.0000
10.500 0.7784 0.06132 0.05574 0.0363 0.0218 1.0000
10.750 0.7599 0.06565 0.06022 0.0361 0.0219 1.0000
11.000 0.6787 0.08585 0.08083 0.0233 0.0258 1.0000
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Polar data table (+)
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