EPPLER 58 AIRFOIL (e58-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 58 AIRFOIL (e58-il) Reynolds number: 50,000 Max Cl/Cd: 44.07 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e58-il-50000-n5.txt Download as CSV file: xf-e58-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 58 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3763 0.12612 0.11977 -0.0198 1.0000 0.0637
-7.250 -0.3847 0.12551 0.11926 -0.0189 1.0000 0.0640
-7.000 -0.3948 0.12508 0.11893 -0.0180 1.0000 0.0643
-6.750 -0.3986 0.12402 0.11795 -0.0192 1.0000 0.0645
-6.500 -0.3775 0.11532 0.10921 -0.0147 1.0000 0.0693
-6.250 -0.3804 0.11338 0.10734 -0.0133 1.0000 0.0721
-6.000 -0.3826 0.11158 0.10560 -0.0130 1.0000 0.0750
-5.750 -0.3843 0.11031 0.10440 -0.0148 1.0000 0.0774
-5.500 -0.3803 0.10930 0.10347 -0.0207 1.0000 0.0786
-5.250 -0.3771 0.10484 0.09908 -0.0180 1.0000 0.0799
-5.000 -0.3730 0.10129 0.09555 -0.0153 1.0000 0.0827
-4.750 -0.3667 0.09849 0.09278 -0.0160 1.0000 0.0861
-4.500 -0.3522 0.09604 0.09035 -0.0223 1.0000 0.0913
-4.250 -0.3311 0.09258 0.08691 -0.0302 1.0000 0.0932
-4.000 -0.3292 0.08897 0.08334 -0.0262 1.0000 0.0953
-3.750 -0.3168 0.08572 0.08006 -0.0272 1.0000 0.0990
-3.500 -0.2581 0.08147 0.07565 -0.0470 0.9995 0.1067
-3.250 -0.2474 0.07728 0.07150 -0.0446 0.9962 0.1089
-2.750 -0.1258 0.06376 0.05749 -0.0726 0.9910 0.0671
-2.250 0.0381 0.04912 0.04190 -0.1074 0.9902 0.0523
-2.000 0.1023 0.04511 0.03745 -0.1183 0.9893 0.0576
-1.750 0.1885 0.03943 0.03074 -0.1333 0.9907 0.0603
-1.500 0.2471 0.03680 0.02736 -0.1409 0.9902 0.0698
-1.250 0.3001 0.03470 0.02442 -0.1464 0.9896 0.0759
-1.000 0.3422 0.03417 0.02344 -0.1498 0.9875 0.0917
-0.750 0.3796 0.03358 0.02258 -0.1519 0.9842 0.0990
-0.500 0.4170 0.03324 0.02190 -0.1538 0.9812 0.1109
-0.250 0.4550 0.03307 0.02152 -0.1561 0.9783 0.1413
0.000 0.4900 0.03305 0.02147 -0.1580 0.9736 0.2065
0.250 0.5267 0.03321 0.02194 -0.1608 0.9698 0.3124
0.500 0.5602 0.03324 0.02223 -0.1625 0.9647 0.3945
0.750 0.5854 0.03238 0.02250 -0.1619 0.9601 0.8084
1.000 0.6136 0.03283 0.02264 -0.1624 0.9514 1.0000
1.250 0.6493 0.03344 0.02294 -0.1644 0.9454 1.0000
1.500 0.6806 0.03390 0.02322 -0.1654 0.9357 1.0000
1.750 0.7161 0.03430 0.02347 -0.1672 0.9261 1.0000
2.000 0.7548 0.03464 0.02369 -0.1694 0.9177 1.0000
2.500 0.8139 0.03535 0.02435 -0.1706 0.8974 1.0000
2.750 0.8503 0.03564 0.02468 -0.1724 0.8902 1.0000
3.000 0.8769 0.03599 0.02509 -0.1725 0.8792 1.0000
3.250 0.9055 0.03626 0.02544 -0.1728 0.8681 1.0000
3.500 0.9358 0.03640 0.02573 -0.1732 0.8564 1.0000
3.750 0.9666 0.03639 0.02585 -0.1736 0.8436 1.0000
4.000 0.9974 0.03624 0.02587 -0.1737 0.8292 1.0000
4.250 1.0286 0.03594 0.02582 -0.1737 0.8138 1.0000
4.500 1.0598 0.03559 0.02569 -0.1736 0.7982 1.0000
4.750 1.0907 0.03519 0.02555 -0.1734 0.7825 1.0000
5.000 1.1198 0.03475 0.02543 -0.1727 0.7646 1.0000
5.250 1.1448 0.03440 0.02538 -0.1712 0.7430 1.0000
5.500 1.1772 0.03350 0.02481 -0.1704 0.7232 1.0000
5.750 1.2042 0.03305 0.02470 -0.1690 0.6975 1.0000
6.000 1.2376 0.03231 0.02440 -0.1683 0.6706 1.0000
6.250 1.2791 0.03107 0.02350 -0.1682 0.6332 1.0000
6.500 1.3190 0.02993 0.02203 -0.1666 0.5215 1.0000
6.750 1.3274 0.03149 0.02258 -0.1621 0.3857 1.0000
7.000 1.3260 0.03395 0.02423 -0.1576 0.2699 1.0000
7.250 1.3251 0.03725 0.02645 -0.1541 0.1288 1.0000
7.500 1.3318 0.04079 0.02937 -0.1515 0.0601 1.0000
7.750 1.3438 0.04335 0.03198 -0.1492 0.0447 1.0000
8.000 1.3555 0.04572 0.03459 -0.1468 0.0390 1.0000
8.250 1.3660 0.04810 0.03714 -0.1444 0.0352 1.0000
8.500 1.3781 0.05047 0.03978 -0.1421 0.0318 1.0000
8.750 1.3914 0.05284 0.04240 -0.1401 0.0287 1.0000
9.000 1.4070 0.05555 0.04527 -0.1383 0.0271 1.0000
9.250 1.4368 0.05880 0.04882 -0.1377 0.0260 1.0000
9.500 1.4674 0.06270 0.05327 -0.1373 0.0250 1.0000
9.750 1.4825 0.06675 0.05788 -0.1355 0.0239 1.0000
10.000 1.4870 0.07077 0.06240 -0.1328 0.0231 1.0000
10.250 1.4849 0.07494 0.06704 -0.1298 0.0226 1.0000
10.500 1.4776 0.07930 0.07183 -0.1268 0.0223 1.0000
10.750 1.4665 0.08387 0.07681 -0.1239 0.0222 1.0000
11.000 1.4528 0.08864 0.08196 -0.1216 0.0222 1.0000
11.250 1.4362 0.09379 0.08747 -0.1198 0.0223 1.0000
11.500 1.4177 0.09926 0.09327 -0.1189 0.0223 1.0000
11.750 1.3984 0.10513 0.09942 -0.1191 0.0225 1.0000
12.000 1.3789 0.11140 0.10597 -0.1204 0.0226 1.0000
12.250 1.3588 0.11835 0.11315 -0.1231 0.0228 1.0000
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Polar data table (+)
Polar graphs
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