LWK 80-100 (lwk80100-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: LWK 80-100 (lwk80100-il) Reynolds number: 100,000 Max Cl/Cd: 59.44 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-lwk80100-il-100000.txt Download as CSV file: xf-lwk80100-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.6061 0.12033 0.11520 -0.0030 1.0000 0.1132
-11.000 -0.6140 0.11602 0.11094 -0.0063 1.0000 0.1187
-10.750 -0.6507 0.11028 0.10539 -0.0159 1.0000 0.1207
-10.500 -0.6122 0.10706 0.10205 -0.0085 1.0000 0.1260
-10.250 -0.6146 0.10289 0.09791 -0.0105 1.0000 0.1308
-10.000 -0.6611 0.09591 0.09110 -0.0219 1.0000 0.1345
-9.750 -0.6297 0.09293 0.08809 -0.0158 1.0000 0.1388
-9.500 -0.6298 0.08886 0.08405 -0.0170 1.0000 0.1436
-9.250 -0.6759 0.08240 0.07767 -0.0249 1.0000 0.1478
-9.000 -0.7412 0.08023 0.07536 -0.0251 1.0000 0.1491
-8.250 -0.7605 0.05431 0.04847 -0.0242 1.0000 0.0822
-8.000 -0.7663 0.04728 0.04052 -0.0201 1.0000 0.0647
-7.750 -0.7590 0.04306 0.03603 -0.0180 1.0000 0.0632
-7.500 -0.7507 0.03938 0.03196 -0.0154 1.0000 0.0623
-7.250 -0.7402 0.03620 0.02835 -0.0128 1.0000 0.0624
-7.000 -0.7292 0.03430 0.02588 -0.0097 1.0000 0.0654
-6.750 -0.7160 0.03115 0.02247 -0.0077 1.0000 0.0685
-6.500 -0.6995 0.02911 0.02027 -0.0058 1.0000 0.0713
-6.250 -0.6842 0.02753 0.01844 -0.0034 1.0000 0.0761
-6.000 -0.6688 0.02577 0.01650 -0.0012 1.0000 0.0822
-5.750 -0.6521 0.02440 0.01504 0.0009 1.0000 0.0887
-5.500 -0.6353 0.02301 0.01359 0.0028 1.0000 0.0971
-5.250 -0.6194 0.02214 0.01255 0.0050 1.0000 0.1069
-5.000 -0.6025 0.02080 0.01134 0.0069 1.0000 0.1180
-4.750 -0.5878 0.01988 0.01044 0.0091 1.0000 0.1349
-4.500 -0.5750 0.01874 0.00954 0.0116 1.0000 0.1536
-4.250 -0.5633 0.01773 0.00877 0.0142 1.0000 0.1865
-4.000 -0.5569 0.01618 0.00796 0.0176 1.0000 0.2750
-3.750 -0.5661 0.01422 0.00815 0.0253 1.0000 0.6259
-3.500 -0.5596 0.01479 0.00890 0.0315 1.0000 0.7520
-3.250 -0.5491 0.01531 0.00932 0.0364 1.0000 0.7997
-3.000 -0.5348 0.01577 0.00969 0.0406 1.0000 0.8331
-2.750 -0.5179 0.01619 0.01001 0.0444 1.0000 0.8646
-2.500 -0.4896 0.01668 0.01036 0.0460 1.0000 0.8930
-2.250 -0.4234 0.01770 0.01112 0.0407 1.0000 0.9204
-2.000 -0.2469 0.01945 0.01239 0.0157 1.0000 0.9516
-1.750 -0.1853 0.01938 0.01216 0.0088 1.0000 0.9646
-1.500 -0.1380 0.01920 0.01187 0.0040 1.0000 0.9748
-1.250 -0.0951 0.01901 0.01160 -0.0001 1.0000 0.9838
-1.000 -0.0524 0.01880 0.01133 -0.0043 1.0000 0.9919
-0.750 -0.0099 0.01862 0.01111 -0.0085 1.0000 0.9992
-0.500 -0.0033 0.01864 0.01111 -0.0063 1.0000 1.0000
-0.250 -0.0017 0.01866 0.01113 -0.0031 1.0000 1.0000
0.000 0.0001 0.01866 0.01114 0.0000 1.0000 1.0000
0.250 0.0019 0.01866 0.01113 0.0032 1.0000 1.0000
0.500 0.0034 0.01864 0.01112 0.0063 1.0000 1.0000
0.750 0.0106 0.01862 0.01111 0.0084 0.9991 1.0000
1.000 0.0527 0.01880 0.01134 0.0043 0.9919 1.0000
1.250 0.0953 0.01901 0.01159 0.0001 0.9838 1.0000
1.500 0.1381 0.01919 0.01187 -0.0040 0.9748 1.0000
1.750 0.1870 0.01937 0.01216 -0.0090 0.9642 1.0000
2.000 0.2496 0.01943 0.01237 -0.0161 0.9509 1.0000
2.250 0.4305 0.01756 0.01099 -0.0417 0.9187 1.0000
2.500 0.4897 0.01669 0.01038 -0.0460 0.8933 1.0000
2.750 0.5182 0.01620 0.01002 -0.0445 0.8651 1.0000
3.000 0.5352 0.01580 0.00973 -0.0408 0.8347 1.0000
3.250 0.5493 0.01530 0.00931 -0.0364 0.7993 1.0000
3.500 0.5603 0.01479 0.00891 -0.0316 0.7536 1.0000
3.750 0.5670 0.01424 0.00823 -0.0256 0.6378 1.0000
4.000 0.5578 0.01609 0.00794 -0.0178 0.2832 1.0000
4.250 0.5637 0.01768 0.00873 -0.0143 0.1908 1.0000
4.500 0.5755 0.01868 0.00951 -0.0116 0.1564 1.0000
4.750 0.5883 0.01975 0.01038 -0.0091 0.1362 1.0000
5.000 0.6028 0.02080 0.01132 -0.0069 0.1196 1.0000
5.250 0.6192 0.02203 0.01248 -0.0050 0.1072 1.0000
5.500 0.6353 0.02299 0.01358 -0.0028 0.0969 1.0000
5.750 0.6520 0.02439 0.01505 -0.0008 0.0880 1.0000
6.000 0.6683 0.02576 0.01643 0.0012 0.0811 1.0000
6.250 0.6633 0.01116 0.00289 0.0046 0.0736 1.0000
6.500 0.6755 0.01287 0.00482 0.0072 0.0704 1.0000
6.750 0.6866 0.01477 0.00679 0.0095 0.0674 1.0000
7.000 0.6926 0.01718 0.00959 0.0127 0.0646 1.0000
7.250 0.6996 0.01951 0.01235 0.0158 0.0630 1.0000
7.500 0.7054 0.02274 0.01598 0.0188 0.0628 1.0000
7.750 0.7103 0.02647 0.02005 0.0213 0.0637 1.0000
8.000 0.7140 0.03085 0.02467 0.0235 0.0649 1.0000
8.250 0.6959 0.03732 0.03197 0.0280 0.0742 1.0000
9.250 0.6662 0.08251 0.07777 0.0241 0.1473 1.0000
9.500 0.6291 0.08900 0.08417 0.0169 0.1421 1.0000
9.750 0.6373 0.09238 0.08755 0.0174 0.1377 1.0000
10.000 0.6581 0.09605 0.09124 0.0212 0.1344 1.0000
10.250 0.6124 0.10314 0.09816 0.0099 0.1290 1.0000
10.500 0.6166 0.10686 0.10185 0.0094 0.1245 1.0000
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Polar data table (+)
Polar graphs
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