LWK 80-080 (lwk80080-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: LWK 80-080 (lwk80080-il) Reynolds number: 1,000,000 Max Cl/Cd: 57.22 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-lwk80080-il-1000000-n5.txt Download as CSV file: xf-lwk80080-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: LWK 80-080
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.000 -0.9267 0.06640 0.06497 -0.0151 1.0000 0.0022
-11.500 -1.0397 0.04233 0.04025 -0.0190 1.0000 0.0019
-11.250 -1.0427 0.03876 0.03646 -0.0174 1.0000 0.0019
-11.000 -1.0739 0.03038 0.02736 -0.0135 1.0000 0.0020
-10.750 -1.0715 0.02687 0.02346 -0.0114 1.0000 0.0022
-10.500 -1.0578 0.02505 0.02142 -0.0101 1.0000 0.0022
-10.250 -1.0333 0.02508 0.02149 -0.0099 1.0000 0.0024
-10.000 -1.0145 0.02404 0.02033 -0.0091 1.0000 0.0025
-9.750 -1.0001 0.02205 0.01807 -0.0077 1.0000 0.0026
-9.500 -0.9804 0.02102 0.01689 -0.0068 1.0000 0.0027
-9.250 -0.9598 0.02012 0.01585 -0.0060 1.0000 0.0028
-9.000 -0.9396 0.01912 0.01470 -0.0051 1.0000 0.0030
-8.750 -0.9183 0.01827 0.01373 -0.0043 1.0000 0.0032
-8.500 -0.8974 0.01734 0.01266 -0.0034 1.0000 0.0034
-8.250 -0.8774 0.01618 0.01133 -0.0022 1.0000 0.0036
-8.000 -0.8560 0.01536 0.01038 -0.0013 1.0000 0.0037
-7.750 -0.8384 0.01505 0.01004 0.0006 0.9963 0.0039
-7.500 -0.8059 0.01417 0.00903 -0.0009 0.9792 0.0040
-7.250 -0.7691 0.01350 0.00822 -0.0033 0.9650 0.0041
-7.000 -0.7302 0.01247 0.00707 -0.0064 0.9557 0.0053
-6.750 -0.6889 0.01207 0.00664 -0.0099 0.9459 0.0059
-6.500 -0.6495 0.01139 0.00584 -0.0129 0.9345 0.0062
-6.250 -0.6135 0.01086 0.00517 -0.0151 0.9215 0.0064
-6.000 -0.5818 0.01051 0.00473 -0.0163 0.9086 0.0068
-5.750 -0.5536 0.01019 0.00429 -0.0166 0.8974 0.0072
-5.500 -0.5273 0.00989 0.00390 -0.0164 0.8878 0.0075
-5.250 -0.5019 0.00959 0.00352 -0.0160 0.8794 0.0076
-4.750 -0.4522 0.00900 0.00285 -0.0149 0.8656 0.0130
-4.500 -0.4270 0.00879 0.00261 -0.0144 0.8598 0.0169
-4.250 -0.4016 0.00861 0.00242 -0.0140 0.8546 0.0205
-4.000 -0.3764 0.00841 0.00221 -0.0135 0.8491 0.0274
-3.500 -0.3257 0.00807 0.00189 -0.0127 0.8399 0.0447
-3.250 -0.3012 0.00783 0.00174 -0.0121 0.8352 0.0666
-3.000 -0.2755 0.00770 0.00159 -0.0117 0.8310 0.0773
-2.750 -0.2519 0.00737 0.00144 -0.0110 0.8270 0.1245
-2.500 -0.2280 0.00709 0.00132 -0.0103 0.8227 0.1691
-2.250 -0.2049 0.00676 0.00118 -0.0094 0.8184 0.2326
-2.000 -0.1834 0.00632 0.00105 -0.0083 0.8143 0.3221
-1.750 -0.1625 0.00586 0.00092 -0.0071 0.8098 0.4204
-1.500 -0.1412 0.00547 0.00080 -0.0058 0.8055 0.5073
-1.250 -0.1215 0.00506 0.00072 -0.0042 0.8015 0.6079
-1.000 -0.0982 0.00487 0.00071 -0.0032 0.7968 0.6608
-0.750 -0.0747 0.00477 0.00071 -0.0022 0.7907 0.7035
-0.500 -0.0501 0.00471 0.00071 -0.0014 0.7822 0.7283
-0.250 -0.0254 0.00469 0.00071 -0.0006 0.7712 0.7485
0.000 0.0000 0.00469 0.00070 0.0000 0.7608 0.7603
0.250 0.0252 0.00470 0.00070 0.0007 0.7465 0.7715
0.500 0.0501 0.00471 0.00071 0.0014 0.7278 0.7822
0.750 0.0745 0.00477 0.00071 0.0022 0.7011 0.7909
1.000 0.0985 0.00486 0.00071 0.0031 0.6649 0.7968
1.250 0.1204 0.00511 0.00072 0.0044 0.5952 0.8015
1.500 0.1405 0.00552 0.00081 0.0060 0.4972 0.8056
1.750 0.1608 0.00598 0.00094 0.0074 0.3933 0.8099
2.000 0.1814 0.00647 0.00108 0.0087 0.2891 0.8145
2.250 0.2042 0.00682 0.00119 0.0096 0.2194 0.8183
2.500 0.2276 0.00713 0.00132 0.0104 0.1616 0.8225
2.750 0.2518 0.00738 0.00145 0.0110 0.1216 0.8269
3.000 0.2752 0.00772 0.00161 0.0117 0.0736 0.8312
3.250 0.2999 0.00794 0.00175 0.0123 0.0494 0.8356
3.500 0.3252 0.00811 0.00190 0.0127 0.0382 0.8401
4.000 0.3759 0.00847 0.00222 0.0136 0.0219 0.8489
4.250 0.4015 0.00862 0.00242 0.0140 0.0194 0.8544
4.500 0.4266 0.00883 0.00263 0.0145 0.0144 0.8597
4.750 0.4516 0.00906 0.00287 0.0150 0.0098 0.8659
5.250 0.5017 0.00962 0.00356 0.0161 0.0075 0.8799
5.500 0.5270 0.00993 0.00396 0.0165 0.0072 0.8879
5.750 0.5537 0.01017 0.00427 0.0165 0.0071 0.8972
6.000 0.5814 0.01056 0.00479 0.0163 0.0065 0.9081
6.250 0.6126 0.01096 0.00530 0.0153 0.0063 0.9208
6.500 0.6489 0.01145 0.00590 0.0131 0.0060 0.9340
6.750 0.6886 0.01211 0.00667 0.0100 0.0057 0.9457
7.000 0.7295 0.01275 0.00742 0.0066 0.0053 0.9558
7.250 0.7695 0.01347 0.00823 0.0033 0.0047 0.9650
7.500 0.8040 0.01484 0.00980 0.0012 0.0041 0.9810
8.000 0.8526 0.01605 0.01117 0.0019 0.0040 1.0000
8.250 0.8762 0.01644 0.01162 0.0024 0.0038 1.0000
8.500 0.8971 0.01742 0.01275 0.0034 0.0035 1.0000
8.750 0.9175 0.01848 0.01398 0.0044 0.0034 1.0000
9.000 0.9359 0.01994 0.01565 0.0056 0.0032 1.0000
9.250 0.9556 0.02108 0.01695 0.0066 0.0030 1.0000
9.500 0.9792 0.02131 0.01724 0.0069 0.0028 1.0000
9.750 0.9940 0.02333 0.01954 0.0084 0.0027 1.0000
10.000 1.0158 0.02383 0.02009 0.0089 0.0025 1.0000
10.250 1.0348 0.02485 0.02123 0.0097 0.0024 1.0000
10.500 1.0400 0.02827 0.02509 0.0119 0.0024 1.0000
10.750 1.0723 0.02678 0.02336 0.0113 0.0022 1.0000
11.000 1.0796 0.02954 0.02645 0.0130 0.0022 1.0000
11.250 1.0835 0.03260 0.02982 0.0149 0.0022 1.0000
11.500 1.0753 0.03720 0.03479 0.0171 0.0019 1.0000
11.750 1.0516 0.04306 0.04103 0.0200 0.0020 1.0000
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Polar data table (+)
Polar graphs
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