LWK 80-080 (lwk80080-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: LWK 80-080 (lwk80080-il) Reynolds number: 50,000 Max Cl/Cd: 22.36 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-lwk80080-il-50000.txt Download as CSV file: xf-lwk80080-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5853 0.09490 0.08814 0.0170 1.0000 0.3866
-8.000 -0.5693 0.09032 0.08357 0.0182 1.0000 0.4065
-7.000 -0.6813 0.05892 0.05177 -0.0173 1.0000 0.1482
-6.750 -0.6809 0.05325 0.04527 -0.0167 1.0000 0.1258
-6.500 -0.6669 0.04921 0.04087 -0.0155 1.0000 0.1225
-6.250 -0.6536 0.04522 0.03654 -0.0140 1.0000 0.1196
-6.000 -0.6400 0.04124 0.03187 -0.0119 1.0000 0.1139
-5.750 -0.6230 0.03829 0.02808 -0.0095 1.0000 0.1110
-5.500 -0.6025 0.03500 0.02438 -0.0078 1.0000 0.1117
-5.250 -0.5814 0.03229 0.02162 -0.0067 1.0000 0.1210
-5.000 -0.5587 0.02978 0.01886 -0.0053 1.0000 0.1307
-4.750 -0.5307 0.02719 0.01597 -0.0042 1.0000 0.1415
-4.500 -0.5040 0.02519 0.01396 -0.0032 1.0000 0.1672
-4.250 -0.4738 0.02292 0.01193 -0.0025 1.0000 0.2041
-4.000 -0.4574 0.02050 0.01017 -0.0003 1.0000 0.2881
-3.750 -0.1791 0.02148 0.01152 -0.0268 1.0000 1.0000
-3.500 -0.1628 0.02087 0.01072 -0.0263 1.0000 1.0000
-3.250 -0.1462 0.02033 0.01001 -0.0257 1.0000 1.0000
-3.000 -0.1295 0.01985 0.00938 -0.0250 1.0000 1.0000
-2.750 -0.1129 0.01943 0.00883 -0.0241 1.0000 1.0000
-2.500 -0.0963 0.01906 0.00832 -0.0232 1.0000 1.0000
-2.250 -0.0802 0.01873 0.00790 -0.0221 1.0000 1.0000
-2.000 -0.0647 0.01844 0.00754 -0.0208 1.0000 1.0000
-1.750 -0.0499 0.01820 0.00726 -0.0194 1.0000 1.0000
-1.500 -0.0364 0.01799 0.00702 -0.0177 1.0000 1.0000
-1.250 -0.0245 0.01782 0.00685 -0.0158 1.0000 1.0000
-1.000 -0.0147 0.01770 0.00674 -0.0134 1.0000 1.0000
-0.750 -0.0072 0.01763 0.00665 -0.0107 1.0000 1.0000
-0.500 -0.0027 0.01760 0.00665 -0.0075 1.0000 1.0000
-0.250 -0.0006 0.01759 0.00664 -0.0039 1.0000 1.0000
0.000 0.0000 0.01758 0.00663 0.0000 1.0000 1.0000
0.250 0.0007 0.01759 0.00664 0.0039 1.0000 1.0000
0.500 0.0027 0.01759 0.00664 0.0075 1.0000 1.0000
0.750 0.0072 0.01763 0.00666 0.0107 1.0000 1.0000
1.000 0.0147 0.01770 0.00672 0.0134 1.0000 1.0000
1.250 0.0246 0.01782 0.00685 0.0158 1.0000 1.0000
1.500 0.0364 0.01798 0.00702 0.0177 1.0000 1.0000
1.750 0.0500 0.01819 0.00726 0.0194 1.0000 1.0000
2.000 0.0647 0.01844 0.00755 0.0208 1.0000 1.0000
2.250 0.0802 0.01873 0.00790 0.0221 1.0000 1.0000
2.500 0.0964 0.01906 0.00835 0.0232 1.0000 1.0000
2.750 0.1129 0.01943 0.00883 0.0241 1.0000 1.0000
3.000 0.1296 0.01985 0.00937 0.0249 1.0000 1.0000
3.250 0.1463 0.02032 0.00999 0.0257 1.0000 1.0000
3.500 0.1629 0.02086 0.01070 0.0263 1.0000 1.0000
3.750 0.1792 0.02148 0.01151 0.0267 1.0000 1.0000
4.000 0.4575 0.02046 0.01015 0.0002 0.2908 1.0000
4.250 0.4738 0.02294 0.01195 0.0025 0.2033 1.0000
4.500 0.5045 0.02530 0.01404 0.0032 0.1663 1.0000
4.750 0.5311 0.02737 0.01608 0.0041 0.1399 1.0000
5.000 0.5586 0.02984 0.01890 0.0053 0.1297 1.0000
5.250 0.5806 0.03222 0.02157 0.0068 0.1184 1.0000
5.500 0.6020 0.03521 0.02461 0.0080 0.1107 1.0000
5.750 0.6227 0.03832 0.02816 0.0097 0.1107 1.0000
6.000 0.6405 0.04161 0.03204 0.0117 0.1121 1.0000
6.250 0.6531 0.04529 0.03662 0.0141 0.1186 1.0000
6.500 0.6657 0.04921 0.04092 0.0156 0.1215 1.0000
6.750 0.6774 0.05335 0.04541 0.0169 0.1234 1.0000
7.000 0.6801 0.05879 0.05156 0.0174 0.1447 1.0000
7.500 0.5415 0.05834 0.05240 0.0100 0.2532 1.0000
7.750 0.5635 0.08699 0.08027 -0.0188 0.4216 1.0000
8.000 0.5762 0.09095 0.08421 -0.0180 0.4038 1.0000
8.250 0.5795 0.09434 0.08755 -0.0171 0.3851 1.0000
8.750 0.5905 0.10138 0.09452 -0.0151 0.3434 1.0000
9.000 0.6115 0.10586 0.09903 -0.0129 0.3180 1.0000
9.250 0.6041 0.10856 0.10164 -0.0132 0.3026 1.0000
9.500 0.6008 0.11134 0.10437 -0.0132 0.2850 1.0000
9.750 0.6243 0.11628 0.10935 -0.0109 0.2634 1.0000
10.000 0.6151 0.11892 0.11191 -0.0121 0.2514 1.0000
10.250 0.6107 0.12209 0.11502 -0.0132 0.2417 1.0000
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Polar data table (+)
Polar graphs
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