EPPLER 395 AIRFOIL (e395-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER 395 AIRFOIL (e395-il) Reynolds number: 200,000 Max Cl/Cd: 92.15 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e395-il-200000.txt Download as CSV file: xf-e395-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 395 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.2421 0.10526 0.10199 -0.0636 0.9834 0.0523
-9.250 -0.2307 0.10105 0.09779 -0.0675 0.9777 0.0542
-9.000 -0.3590 0.05638 0.05302 -0.1010 0.9598 0.0205
-8.750 -0.2293 0.08479 0.08157 -0.0818 0.9663 0.0409
-8.500 -0.2068 0.08349 0.08027 -0.0850 0.9619 0.0506
-8.250 -0.3243 0.03251 0.02751 -0.1382 0.9321 0.0211
-8.000 -0.3001 0.03169 0.02674 -0.1391 0.9258 0.0229
-7.750 -0.2699 0.02849 0.02298 -0.1427 0.9212 0.0245
-7.500 -0.2335 0.02509 0.01903 -0.1466 0.9190 0.0263
-7.250 -0.1937 0.02325 0.01704 -0.1500 0.9176 0.0300
-7.000 -0.1529 0.02161 0.01524 -0.1535 0.9162 0.0365
-6.750 -0.1328 0.02079 0.01434 -0.1528 0.9077 0.0436
-6.500 -0.0947 0.01980 0.01323 -0.1554 0.9051 0.0551
-6.250 -0.0551 0.01887 0.01217 -0.1582 0.9031 0.0676
-6.000 -0.0228 0.01811 0.01134 -0.1595 0.8988 0.0790
-5.750 0.0053 0.01748 0.01066 -0.1599 0.8929 0.0903
-5.500 0.0417 0.01678 0.00990 -0.1618 0.8897 0.1046
-5.250 0.0796 0.01614 0.00918 -0.1640 0.8872 0.1215
-5.000 0.1044 0.01584 0.00886 -0.1636 0.8804 0.1370
-4.750 0.1370 0.01539 0.00838 -0.1647 0.8760 0.1561
-4.500 0.1725 0.01496 0.00795 -0.1664 0.8728 0.1777
-4.250 0.1997 0.01480 0.00776 -0.1664 0.8669 0.1985
-4.000 0.2293 0.01455 0.00754 -0.1669 0.8616 0.2198
-3.750 0.2631 0.01430 0.00725 -0.1681 0.8580 0.2441
-3.500 0.2909 0.01418 0.00716 -0.1682 0.8526 0.2658
-3.250 0.3189 0.01408 0.00706 -0.1683 0.8469 0.2885
-3.000 0.3515 0.01389 0.00686 -0.1692 0.8430 0.3125
-2.750 0.3793 0.01384 0.00682 -0.1693 0.8378 0.3356
-2.500 0.4066 0.01378 0.00679 -0.1692 0.8320 0.3585
-2.250 0.4382 0.01364 0.00665 -0.1699 0.8279 0.3836
-2.000 0.4659 0.01362 0.00667 -0.1700 0.8228 0.4075
-1.750 0.4927 0.01361 0.00669 -0.1698 0.8170 0.4330
-1.500 0.5237 0.01348 0.00661 -0.1703 0.8128 0.4600
-1.250 0.5511 0.01349 0.00667 -0.1703 0.8077 0.4875
-1.000 0.5775 0.01349 0.00675 -0.1700 0.8018 0.5164
-0.750 0.6080 0.01340 0.00670 -0.1704 0.7976 0.5481
-0.500 0.6345 0.01343 0.00683 -0.1701 0.7923 0.5805
-0.250 0.6604 0.01343 0.00694 -0.1697 0.7864 0.6145
0.000 0.6901 0.01335 0.00692 -0.1698 0.7822 0.6526
0.250 0.7144 0.01340 0.00710 -0.1690 0.7765 0.6901
0.500 0.7390 0.01340 0.00721 -0.1682 0.7707 0.7313
0.750 0.7658 0.01330 0.00719 -0.1675 0.7665 0.7760
1.000 0.7839 0.01335 0.00740 -0.1653 0.7601 0.8236
1.250 0.8010 0.01323 0.00739 -0.1625 0.7545 0.8847
1.500 0.8316 0.01302 0.00716 -0.1627 0.7505 1.0000
1.750 0.8572 0.01326 0.00739 -0.1627 0.7432 1.0000
2.000 0.8886 0.01333 0.00740 -0.1634 0.7381 1.0000
2.250 0.9186 0.01346 0.00747 -0.1639 0.7327 1.0000
2.500 0.9450 0.01362 0.00764 -0.1638 0.7258 1.0000
2.750 0.9772 0.01365 0.00760 -0.1645 0.7209 1.0000
3.000 1.0016 0.01387 0.00785 -0.1640 0.7134 1.0000
3.250 1.0315 0.01391 0.00786 -0.1643 0.7074 1.0000
3.500 1.0583 0.01406 0.00803 -0.1642 0.7004 1.0000
3.750 1.0861 0.01413 0.00810 -0.1641 0.6932 1.0000
4.000 1.1139 0.01422 0.00820 -0.1640 0.6862 1.0000
4.250 1.1406 0.01429 0.00829 -0.1637 0.6781 1.0000
4.500 1.1673 0.01438 0.00840 -0.1634 0.6702 1.0000
4.750 1.1948 0.01441 0.00844 -0.1632 0.6619 1.0000
5.000 1.2191 0.01453 0.00863 -0.1625 0.6526 1.0000
5.250 1.2490 0.01452 0.00858 -0.1627 0.6446 1.0000
5.500 1.2707 0.01465 0.00881 -0.1615 0.6338 1.0000
5.750 1.2952 0.01474 0.00895 -0.1607 0.6235 1.0000
6.000 1.3212 0.01478 0.00900 -0.1602 0.6129 1.0000
6.250 1.3443 0.01486 0.00912 -0.1591 0.6006 1.0000
6.500 1.3657 0.01498 0.00931 -0.1578 0.5870 1.0000
6.750 1.3869 0.01512 0.00950 -0.1564 0.5725 1.0000
7.000 1.4076 0.01528 0.00969 -0.1549 0.5567 1.0000
7.250 1.4274 0.01549 0.00990 -0.1533 0.5394 1.0000
7.500 1.4439 0.01577 0.01024 -0.1511 0.5195 1.0000
7.750 1.4593 0.01611 0.01058 -0.1487 0.4978 1.0000
8.000 1.4723 0.01654 0.01098 -0.1460 0.4735 1.0000
8.250 1.4816 0.01707 0.01145 -0.1426 0.4464 1.0000
8.500 1.4863 0.01773 0.01201 -0.1384 0.4173 1.0000
8.750 1.4887 0.01856 0.01273 -0.1341 0.3856 1.0000
9.000 1.4890 0.01959 0.01362 -0.1297 0.3524 1.0000
9.250 1.4875 0.02082 0.01471 -0.1253 0.3194 1.0000
9.500 1.4851 0.02225 0.01601 -0.1212 0.2875 1.0000
9.750 1.4822 0.02387 0.01748 -0.1173 0.2569 1.0000
10.000 1.4795 0.02564 0.01912 -0.1137 0.2274 1.0000
10.250 1.4770 0.02755 0.02091 -0.1105 0.1992 1.0000
10.500 1.4744 0.02963 0.02286 -0.1076 0.1719 1.0000
10.750 1.4721 0.03183 0.02495 -0.1049 0.1466 1.0000
11.000 1.4689 0.03424 0.02724 -0.1025 0.1234 1.0000
11.250 1.4658 0.03677 0.02966 -0.1002 0.1025 1.0000
11.500 1.4621 0.03949 0.03229 -0.0981 0.0856 1.0000
11.750 1.4593 0.04226 0.03504 -0.0963 0.0712 1.0000
12.000 1.4556 0.04522 0.03798 -0.0946 0.0604 1.0000
12.250 1.4498 0.04853 0.04124 -0.0930 0.0524 1.0000
12.500 1.4503 0.05130 0.04409 -0.0918 0.0452 1.0000
12.750 1.4470 0.05458 0.04744 -0.0907 0.0399 1.0000
13.000 1.4444 0.05789 0.05077 -0.0898 0.0356 1.0000
13.250 1.4422 0.06128 0.05427 -0.0889 0.0321 1.0000
13.500 1.4416 0.06454 0.05758 -0.0884 0.0289 1.0000
13.750 1.4383 0.06823 0.06133 -0.0878 0.0264 1.0000
14.000 1.4403 0.07135 0.06458 -0.0875 0.0239 1.0000
14.250 1.4388 0.07492 0.06815 -0.0873 0.0222 1.0000
14.500 1.4403 0.07821 0.07158 -0.0866 0.0208 1.0000
14.750 1.4433 0.08137 0.07489 -0.0864 0.0193 1.0000
15.000 1.4452 0.08467 0.07824 -0.0865 0.0181 1.0000
15.250 1.4486 0.08775 0.08132 -0.0861 0.0168 1.0000
15.500 1.4488 0.09148 0.08530 -0.0865 0.0158 1.0000
15.750 1.4501 0.09505 0.08903 -0.0869 0.0149 1.0000
16.000 1.4519 0.09855 0.09265 -0.0873 0.0143 1.0000
16.250 1.4547 0.10188 0.09606 -0.0877 0.0137 1.0000
16.500 1.4622 0.10468 0.09890 -0.0870 0.0132 1.0000
16.750 1.4564 0.10956 0.10406 -0.0884 0.0130 1.0000
17.000 1.4499 0.11468 0.10947 -0.0900 0.0128 1.0000
17.250 1.4416 0.12023 0.11529 -0.0921 0.0127 1.0000
17.500 1.4319 0.12614 0.12146 -0.0946 0.0126 1.0000
17.750 1.4211 0.13239 0.12796 -0.0977 0.0126 1.0000
18.000 1.4092 0.13900 0.13482 -0.1012 0.0126 1.0000
18.250 1.3958 0.14617 0.14223 -0.1054 0.0126 1.0000
18.500 1.3820 0.15367 0.14995 -0.1101 0.0126 1.0000
18.750 1.3674 0.16169 0.15818 -0.1155 0.0127 1.0000
19.000 1.3527 0.17004 0.16671 -0.1212 0.0128 1.0000
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