EPPLER 49 AIRFOIL (e49-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 49 AIRFOIL (e49-il) Reynolds number: 1,000,000 Max Cl/Cd: 123.08 at α=0.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e49-il-1000000-n5.txt Download as CSV file: xf-e49-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 49 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.0018 0.10088 0.09885 -0.1315 0.9302 0.0037
-10.750 0.0042 0.09884 0.09680 -0.1316 0.9289 0.0044
-10.500 0.0106 0.09647 0.09444 -0.1320 0.9279 0.0046
-10.250 0.0174 0.09396 0.09194 -0.1328 0.9271 0.0047
-7.000 0.0414 0.07014 0.06825 -0.1237 0.9006 0.0059
-6.750 0.0570 0.06662 0.06474 -0.1270 0.8988 0.0059
-6.500 0.0768 0.06274 0.06084 -0.1314 0.8976 0.0059
-6.250 0.0949 0.05577 0.05384 -0.1384 0.8965 0.0052
-6.000 0.1254 0.05052 0.04855 -0.1463 0.8959 0.0050
-5.500 0.2290 0.03399 0.03171 -0.1737 0.8952 0.0068
-5.250 0.2595 0.03261 0.03028 -0.1765 0.8949 0.0074
-5.000 0.2590 0.03238 0.03003 -0.1721 0.8889 0.0078
-4.750 0.2841 0.03094 0.02853 -0.1735 0.8868 0.0088
-4.500 0.3214 0.02814 0.02556 -0.1777 0.8860 0.0099
-4.250 0.3604 0.02535 0.02257 -0.1818 0.8856 0.0109
-4.000 0.4034 0.02200 0.01890 -0.1862 0.8856 0.0103
-3.750 0.4436 0.01917 0.01571 -0.1894 0.8855 0.0097
-3.500 0.4807 0.01692 0.01307 -0.1917 0.8852 0.0091
-3.250 0.5154 0.01513 0.01094 -0.1932 0.8847 0.0087
-3.000 0.5481 0.01380 0.00929 -0.1943 0.8841 0.0084
-2.250 0.3910 0.00868 0.00215 -0.1243 0.9010 0.0368
-1.750 0.5195 0.02327 0.02054 -0.2608 0.9282 0.0085
-0.750 0.8007 0.01030 0.00543 -0.1960 0.8641 0.0195
0.250 0.9037 0.00975 0.00482 -0.1949 0.8390 0.0171
0.750 0.9994 0.00812 0.00327 -0.2039 0.7760 0.2657
1.000 1.0000 0.00882 0.00364 -0.1982 0.7015 0.3241
1.250 1.0111 0.00917 0.00407 -0.1950 0.6689 0.4512
1.750 1.0406 0.00910 0.00488 -0.1901 0.6229 1.0000
2.000 1.0392 0.01019 0.00548 -0.1844 0.5299 1.0000
2.250 1.0336 0.01207 0.00628 -0.1783 0.3307 1.0000
2.750 1.0508 0.01516 0.00776 -0.1721 0.0063 1.0000
3.000 1.0736 0.01542 0.00797 -0.1714 0.0049 1.0000
3.250 1.0965 0.01568 0.00820 -0.1708 0.0028 1.0000
3.500 1.1190 0.01596 0.00851 -0.1700 0.0022 1.0000
3.750 1.1413 0.01627 0.00885 -0.1692 0.0021 1.0000
4.000 1.1634 0.01660 0.00927 -0.1684 0.0022 1.0000
4.250 1.1849 0.01698 0.00970 -0.1675 0.0022 1.0000
4.500 1.2058 0.01742 0.01018 -0.1664 0.0023 1.0000
4.750 1.2260 0.01790 0.01072 -0.1652 0.0025 1.0000
5.000 1.2457 0.01843 0.01129 -0.1640 0.0027 1.0000
5.250 1.2649 0.01901 0.01193 -0.1626 0.0030 1.0000
5.500 1.2832 0.01971 0.01270 -0.1610 0.0036 1.0000
5.750 1.2997 0.02061 0.01373 -0.1590 0.0046 1.0000
6.000 1.3139 0.02171 0.01496 -0.1565 0.0058 1.0000
9.000 1.5268 0.03973 0.03423 -0.1397 0.0033 1.0000
9.250 1.5350 0.04175 0.03640 -0.1372 0.0030 1.0000
9.500 1.5406 0.04394 0.03877 -0.1344 0.0029 1.0000
9.750 1.5432 0.04634 0.04134 -0.1313 0.0027 1.0000
10.000 1.5438 0.04899 0.04417 -0.1281 0.0026 1.0000
10.250 1.5415 0.05197 0.04733 -0.1247 0.0024 1.0000
10.500 1.5362 0.05529 0.05085 -0.1211 0.0023 1.0000
10.750 1.5265 0.05906 0.05484 -0.1174 0.0023 1.0000
11.000 1.5134 0.06322 0.05922 -0.1137 0.0022 1.0000
11.250 1.4977 0.06764 0.06387 -0.1103 0.0021 1.0000
11.500 1.4795 0.07242 0.06886 -0.1073 0.0021 1.0000
11.750 1.4609 0.07734 0.07399 -0.1049 0.0021 1.0000
12.000 1.4420 0.08249 0.07934 -0.1032 0.0020 1.0000
12.250 1.4223 0.08804 0.08507 -0.1023 0.0020 1.0000
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Polar data table (+)
Polar graphs
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