Supermarine 371-II (tip) (supermarine371ii-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: Supermarine 371-II (tip) (supermarine371ii-il) Reynolds number: 50,000 Max Cl/Cd: 19.2 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-supermarine371ii-il-50000.txt Download as CSV file: xf-supermarine371ii-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: Supermarine 371-II (tip)
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.5348 0.10164 0.09517 -0.0049 1.0000 0.2782
-8.500 -0.5477 0.09946 0.09311 -0.0056 1.0000 0.2951
-8.250 -0.5379 0.09581 0.08941 -0.0038 1.0000 0.3218
-8.000 -0.5145 0.09145 0.08502 -0.0010 1.0000 0.3558
-7.750 -0.5176 0.08920 0.08286 0.0010 1.0000 0.3895
-7.500 -0.4887 0.08498 0.07860 0.0045 1.0000 0.4372
-7.250 -0.4711 0.08187 0.07550 0.0079 1.0000 0.4888
-7.000 -0.4498 0.07907 0.07269 0.0116 1.0000 0.5514
-6.750 -0.4033 0.07452 0.06805 0.0135 1.0000 0.6286
-6.000 -0.4091 0.05220 0.04673 -0.0001 1.0000 0.4755
-5.750 -0.4611 0.05006 0.04490 0.0025 1.0000 0.4582
-5.500 -0.5521 0.05915 0.05370 0.0053 1.0000 0.4585
-5.250 -0.5843 0.05329 0.04756 -0.0055 1.0000 0.3766
-5.000 -0.5445 0.04535 0.03779 -0.0193 1.0000 0.1812
-4.750 -0.5226 0.04175 0.03336 -0.0181 1.0000 0.1409
-4.500 -0.5017 0.03919 0.02981 -0.0159 1.0000 0.1191
-4.250 -0.4826 0.03586 0.02625 -0.0143 1.0000 0.1119
-4.000 -0.4624 0.03351 0.02340 -0.0126 1.0000 0.1104
-3.750 -0.4412 0.03139 0.02091 -0.0111 1.0000 0.1131
-3.500 -0.4169 0.02928 0.01838 -0.0096 1.0000 0.1116
-3.250 -0.1149 0.01982 0.01088 -0.0395 1.0000 1.0000
-3.000 -0.1100 0.01974 0.01055 -0.0366 1.0000 1.0000
-2.750 -0.1081 0.01973 0.01034 -0.0333 1.0000 1.0000
-2.500 -0.1078 0.01973 0.01016 -0.0296 1.0000 1.0000
-2.250 -0.1080 0.01972 0.00998 -0.0259 1.0000 1.0000
-2.000 -0.1078 0.01969 0.00972 -0.0222 1.0000 1.0000
-1.750 -0.1072 0.01964 0.00952 -0.0185 1.0000 1.0000
-1.500 -0.1063 0.01958 0.00931 -0.0150 1.0000 1.0000
-1.250 -0.1048 0.01949 0.00909 -0.0114 1.0000 1.0000
-1.000 -0.1027 0.01940 0.00887 -0.0079 1.0000 1.0000
-0.750 -0.0995 0.01930 0.00865 -0.0046 1.0000 1.0000
-0.500 -0.0942 0.01923 0.00844 -0.0016 1.0000 1.0000
-0.250 -0.0866 0.01920 0.00827 0.0010 1.0000 1.0000
0.000 -0.0762 0.01921 0.00815 0.0032 1.0000 1.0000
0.250 -0.0630 0.01929 0.00805 0.0049 1.0000 1.0000
0.500 -0.0479 0.01941 0.00805 0.0063 1.0000 1.0000
0.750 -0.0314 0.01957 0.00812 0.0074 1.0000 1.0000
1.000 -0.0139 0.01977 0.00824 0.0083 1.0000 1.0000
1.250 0.0043 0.02001 0.00841 0.0091 1.0000 1.0000
1.500 0.0230 0.02027 0.00865 0.0098 1.0000 1.0000
1.750 0.0421 0.02057 0.00895 0.0105 1.0000 1.0000
2.000 0.0614 0.02090 0.00927 0.0110 1.0000 1.0000
2.250 0.0808 0.02125 0.00965 0.0115 1.0000 1.0000
2.500 0.1003 0.02164 0.01009 0.0120 1.0000 1.0000
2.750 0.1199 0.02206 0.01057 0.0124 1.0000 1.0000
3.000 0.1394 0.02251 0.01113 0.0128 1.0000 1.0000
3.250 0.1588 0.02300 0.01174 0.0131 1.0000 1.0000
3.500 0.1781 0.02353 0.01248 0.0134 1.0000 1.0000
3.750 0.1973 0.02410 0.01322 0.0137 1.0000 1.0000
4.000 0.2162 0.02472 0.01404 0.0139 1.0000 1.0000
4.250 0.2349 0.02540 0.01494 0.0141 1.0000 1.0000
4.500 0.2532 0.02613 0.01593 0.0143 1.0000 1.0000
4.750 0.2710 0.02693 0.01704 0.0144 1.0000 1.0000
5.000 0.2885 0.02782 0.01837 0.0144 1.0000 1.0000
5.250 0.6258 0.03260 0.02125 -0.0056 0.0975 1.0000
5.500 0.6543 0.03534 0.02458 -0.0042 0.0995 1.0000
5.750 0.6801 0.03864 0.02846 -0.0027 0.1045 1.0000
6.000 0.7044 0.04277 0.03279 -0.0018 0.1094 1.0000
6.250 0.7232 0.04580 0.03672 0.0005 0.1195 1.0000
6.500 0.7408 0.04962 0.04120 0.0022 0.1316 1.0000
6.750 0.7571 0.05411 0.04644 0.0033 0.1567 1.0000
7.000 0.7700 0.06229 0.05597 -0.0023 0.2722 1.0000
7.250 0.7259 0.07050 0.06454 -0.0124 0.3422 1.0000
7.500 0.6845 0.07770 0.07159 -0.0198 0.3804 1.0000
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Polar data table (+)
Polar graphs
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