LWK 80-120/K25 (lwk80120k25-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: LWK 80-120/K25 (lwk80120k25-il) Reynolds number: 50,000 Max Cl/Cd: 27.35 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-lwk80120k25-il-50000.txt Download as CSV file: xf-lwk80120k25-il-50000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.6496 0.08828 0.08122 -0.0293 1.0000 0.1667
-10.000 -0.6982 0.07887 0.07185 -0.0348 1.0000 0.1509
-9.750 -0.7349 0.07342 0.06637 -0.0347 1.0000 0.1456
-9.500 -0.7844 0.06896 0.06164 -0.0320 1.0000 0.1394
-9.250 -0.7883 0.06443 0.05698 -0.0305 1.0000 0.1374
-9.000 -0.7963 0.06032 0.05265 -0.0283 1.0000 0.1356
-8.750 -0.8039 0.05658 0.04861 -0.0256 1.0000 0.1355
-8.500 -0.8091 0.05323 0.04492 -0.0225 1.0000 0.1367
-8.250 -0.8123 0.05009 0.04134 -0.0191 1.0000 0.1381
-8.000 -0.8130 0.04720 0.03802 -0.0156 1.0000 0.1393
-7.750 -0.8117 0.04455 0.03487 -0.0118 1.0000 0.1406
-7.500 -0.7969 0.04181 0.03225 -0.0102 1.0000 0.1469
-7.250 -0.7913 0.03977 0.02985 -0.0068 1.0000 0.1527
-7.000 -0.7812 0.03741 0.02718 -0.0040 1.0000 0.1581
-6.750 -0.7668 0.03551 0.02513 -0.0017 1.0000 0.1667
-6.500 -0.7513 0.03363 0.02314 0.0003 1.0000 0.1778
-6.250 -0.7322 0.03176 0.02111 0.0020 1.0000 0.1896
-6.000 -0.7120 0.03017 0.01951 0.0034 1.0000 0.2072
-5.750 -0.6883 0.02861 0.01790 0.0045 1.0000 0.2295
-5.500 -0.6643 0.02707 0.01662 0.0056 1.0000 0.2623
-5.250 -0.6454 0.02543 0.01541 0.0074 1.0000 0.3093
-5.000 -0.6408 0.02344 0.01429 0.0115 1.0000 0.3905
-4.750 -0.6340 0.02439 0.01728 0.0227 1.0000 0.6827
-4.500 -0.6037 0.02815 0.02068 0.0304 1.0000 0.7725
-4.250 -0.3336 0.03409 0.02502 0.0034 1.0000 0.8817
-4.000 -0.2042 0.03271 0.02299 -0.0134 1.0000 0.9345
-3.750 -0.1309 0.03106 0.02101 -0.0232 1.0000 0.9693
-3.500 -0.0480 0.02869 0.01834 -0.0357 1.0000 0.9979
-3.250 -0.0347 0.02815 0.01773 -0.0354 1.0000 1.0000
-3.000 -0.0298 0.02790 0.01745 -0.0334 1.0000 1.0000
-2.750 -0.0270 0.02777 0.01729 -0.0309 1.0000 1.0000
-2.500 -0.0257 0.02771 0.01720 -0.0281 1.0000 1.0000
-2.250 -0.0249 0.02769 0.01713 -0.0251 1.0000 1.0000
-2.000 -0.0238 0.02768 0.01709 -0.0222 1.0000 1.0000
-1.750 -0.0222 0.02766 0.01704 -0.0192 1.0000 1.0000
-1.500 -0.0200 0.02764 0.01699 -0.0164 1.0000 1.0000
-1.250 -0.0174 0.02763 0.01695 -0.0136 1.0000 1.0000
-1.000 -0.0144 0.02761 0.01690 -0.0108 1.0000 1.0000
-0.750 -0.0110 0.02759 0.01687 -0.0081 1.0000 1.0000
-0.500 -0.0074 0.02758 0.01685 -0.0054 1.0000 1.0000
-0.250 -0.0037 0.02757 0.01683 -0.0027 1.0000 1.0000
0.000 0.0000 0.02757 0.01683 0.0000 1.0000 1.0000
0.250 0.0038 0.02757 0.01683 0.0027 1.0000 1.0000
0.500 0.0075 0.02758 0.01684 0.0054 1.0000 1.0000
0.750 0.0111 0.02759 0.01687 0.0081 1.0000 1.0000
1.000 0.0144 0.02760 0.01690 0.0108 1.0000 1.0000
1.250 0.0175 0.02762 0.01694 0.0136 1.0000 1.0000
1.500 0.0201 0.02763 0.01698 0.0164 1.0000 1.0000
1.750 0.0222 0.02765 0.01702 0.0192 1.0000 1.0000
2.000 0.0239 0.02767 0.01707 0.0222 1.0000 1.0000
2.250 0.0250 0.02768 0.01712 0.0251 1.0000 1.0000
2.500 0.0258 0.02770 0.01717 0.0281 1.0000 1.0000
2.750 0.0270 0.02775 0.01726 0.0309 1.0000 1.0000
3.000 0.0299 0.02788 0.01743 0.0334 1.0000 1.0000
3.250 0.0348 0.02813 0.01771 0.0354 1.0000 1.0000
3.500 0.0495 0.02871 0.01837 0.0355 0.9975 1.0000
3.750 0.1321 0.03107 0.02102 0.0230 0.9690 1.0000
4.000 0.2041 0.03269 0.02297 0.0134 0.9346 1.0000
4.250 0.3150 0.03403 0.02488 -0.0006 0.8851 1.0000
4.500 0.6036 0.02815 0.02068 -0.0303 0.7724 1.0000
4.750 0.6341 0.02438 0.01727 -0.0228 0.6831 1.0000
5.000 0.6407 0.02343 0.01428 -0.0115 0.3905 1.0000
5.250 0.6454 0.02541 0.01540 -0.0074 0.3099 1.0000
5.500 0.6643 0.02707 0.01661 -0.0056 0.2621 1.0000
5.750 0.6880 0.02860 0.01789 -0.0045 0.2294 1.0000
6.000 0.7120 0.03018 0.01951 -0.0034 0.2069 1.0000
6.250 0.7319 0.03175 0.02106 -0.0019 0.1895 1.0000
6.500 0.7511 0.03362 0.02313 -0.0002 0.1776 1.0000
6.750 0.7666 0.03550 0.02512 0.0018 0.1666 1.0000
7.000 0.7813 0.03742 0.02718 0.0040 0.1579 1.0000
7.250 0.7916 0.03979 0.02986 0.0067 0.1529 1.0000
7.500 0.7968 0.04184 0.03229 0.0102 0.1471 1.0000
7.750 0.8119 0.04454 0.03485 0.0118 0.1406 1.0000
8.000 0.8130 0.04721 0.03803 0.0156 0.1393 1.0000
8.250 0.8114 0.05008 0.04138 0.0193 0.1377 1.0000
8.500 0.8086 0.05320 0.04489 0.0226 0.1364 1.0000
8.750 0.8036 0.05660 0.04864 0.0256 0.1352 1.0000
9.000 0.7962 0.06035 0.05268 0.0283 0.1356 1.0000
9.250 0.7872 0.06450 0.05706 0.0306 0.1372 1.0000
9.500 0.7849 0.06899 0.06167 0.0319 0.1395 1.0000
9.750 0.7343 0.07351 0.06646 0.0347 0.1457 1.0000
10.000 0.6987 0.07898 0.07195 0.0348 0.1511 1.0000
10.250 0.6491 0.08846 0.08141 0.0291 0.1666 1.0000
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Polar data table (+)
Polar graphs
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