EPPLER 396 AIRFOIL (e396-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 396 AIRFOIL (e396-il) Reynolds number: 500,000 Max Cl/Cd: 128.13 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e396-il-500000-n5.txt Download as CSV file: xf-e396-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 396 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.250 -0.3890 0.09938 0.09682 -0.0736 0.9912 0.0048
-13.000 -0.4157 0.08813 0.08547 -0.0808 0.9875 0.0048
-12.750 -0.4368 0.07809 0.07531 -0.0885 0.9833 0.0046
-12.250 -0.4810 0.06099 0.05799 -0.1016 0.9594 0.0044
-12.000 -0.4988 0.05045 0.04726 -0.1135 0.9462 0.0044
-11.750 -0.4963 0.03977 0.03631 -0.1301 0.9335 0.0044
-11.500 -0.4850 0.03079 0.02698 -0.1461 0.9132 0.0045
-11.250 -0.4752 0.02580 0.02162 -0.1554 0.8913 0.0045
-11.000 -0.4628 0.02373 0.01931 -0.1572 0.8774 0.0046
-10.750 -0.4462 0.02232 0.01770 -0.1580 0.8665 0.0047
-10.500 -0.4282 0.02103 0.01620 -0.1585 0.8568 0.0049
-10.250 -0.4086 0.01991 0.01489 -0.1588 0.8478 0.0051
-10.000 -0.3874 0.01892 0.01371 -0.1591 0.8401 0.0053
-9.750 -0.3648 0.01809 0.01272 -0.1593 0.8327 0.0054
-9.500 -0.3417 0.01721 0.01168 -0.1595 0.8259 0.0056
-9.250 -0.3181 0.01637 0.01070 -0.1597 0.8191 0.0061
-9.000 -0.2932 0.01574 0.00995 -0.1599 0.8133 0.0065
-8.750 -0.2677 0.01518 0.00929 -0.1601 0.8073 0.0073
-8.500 -0.2417 0.01469 0.00865 -0.1602 0.8017 0.0080
-8.250 -0.2158 0.01405 0.00792 -0.1605 0.7963 0.0093
-8.000 -0.1893 0.01358 0.00736 -0.1606 0.7909 0.0107
-7.500 -0.1354 0.01270 0.00632 -0.1611 0.7811 0.0153
-7.250 -0.1082 0.01231 0.00589 -0.1613 0.7761 0.0189
-6.750 -0.0530 0.01170 0.00517 -0.1617 0.7672 0.0279
-6.500 -0.0253 0.01139 0.00484 -0.1619 0.7625 0.0332
-6.250 0.0026 0.01114 0.00454 -0.1621 0.7582 0.0392
-6.000 0.0306 0.01090 0.00428 -0.1624 0.7540 0.0466
-5.750 0.0587 0.01064 0.00401 -0.1626 0.7496 0.0547
-5.500 0.0868 0.01045 0.00378 -0.1628 0.7453 0.0622
-5.250 0.1151 0.01027 0.00357 -0.1631 0.7415 0.0714
-5.000 0.1434 0.01006 0.00337 -0.1633 0.7372 0.0823
-4.750 0.1717 0.00989 0.00319 -0.1635 0.7330 0.0930
-4.500 0.2001 0.00976 0.00302 -0.1637 0.7291 0.1037
-4.250 0.2286 0.00961 0.00288 -0.1640 0.7252 0.1167
-4.000 0.2570 0.00949 0.00276 -0.1642 0.7211 0.1290
-3.750 0.2855 0.00937 0.00263 -0.1644 0.7171 0.1440
-3.500 0.3139 0.00927 0.00253 -0.1646 0.7135 0.1598
-3.250 0.3425 0.00916 0.00245 -0.1649 0.7095 0.1759
-3.000 0.3709 0.00907 0.00238 -0.1651 0.7054 0.1905
-2.750 0.3993 0.00900 0.00231 -0.1653 0.7016 0.2076
-2.500 0.4278 0.00894 0.00225 -0.1655 0.6979 0.2235
-2.250 0.4563 0.00887 0.00222 -0.1657 0.6938 0.2405
-2.000 0.4847 0.00883 0.00218 -0.1658 0.6897 0.2560
-1.750 0.5130 0.00880 0.00215 -0.1660 0.6859 0.2732
-1.500 0.5414 0.00876 0.00214 -0.1662 0.6819 0.2899
-1.250 0.5698 0.00871 0.00213 -0.1664 0.6777 0.3078
-1.000 0.5980 0.00869 0.00213 -0.1665 0.6735 0.3253
-0.750 0.6262 0.00868 0.00214 -0.1666 0.6697 0.3439
-0.500 0.6545 0.00866 0.00216 -0.1668 0.6652 0.3635
-0.250 0.6826 0.00864 0.00218 -0.1669 0.6607 0.3828
0.000 0.7106 0.00864 0.00221 -0.1670 0.6565 0.4034
0.250 0.7387 0.00863 0.00226 -0.1671 0.6521 0.4248
0.500 0.7667 0.00862 0.00231 -0.1672 0.6474 0.4471
0.750 0.7944 0.00864 0.00236 -0.1673 0.6428 0.4705
1.000 0.8223 0.00864 0.00243 -0.1674 0.6382 0.4950
1.250 0.8501 0.00864 0.00250 -0.1674 0.6330 0.5207
1.500 0.8775 0.00867 0.00258 -0.1674 0.6282 0.5476
1.750 0.9051 0.00868 0.00267 -0.1674 0.6229 0.5756
2.000 0.9323 0.00870 0.00277 -0.1674 0.6171 0.6047
2.250 0.9592 0.00874 0.00287 -0.1672 0.6116 0.6351
2.500 0.9862 0.00875 0.00298 -0.1671 0.6052 0.6669
2.750 1.0124 0.00880 0.00310 -0.1668 0.5989 0.6999
3.000 1.0387 0.00882 0.00323 -0.1665 0.5921 0.7355
3.250 1.0636 0.00887 0.00336 -0.1660 0.5846 0.7732
3.500 1.0878 0.00889 0.00351 -0.1652 0.5762 0.8163
3.750 1.1086 0.00891 0.00363 -0.1637 0.5677 0.8690
4.000 1.1285 0.00885 0.00368 -0.1618 0.5589 1.0000
4.250 1.1541 0.00901 0.00382 -0.1615 0.5497 1.0000
4.500 1.1788 0.00920 0.00398 -0.1610 0.5392 1.0000
4.750 1.2032 0.00940 0.00415 -0.1604 0.5276 1.0000
5.000 1.2276 0.00960 0.00433 -0.1599 0.5161 1.0000
5.250 1.2513 0.00982 0.00454 -0.1592 0.5046 1.0000
5.500 1.2741 0.01007 0.00476 -0.1583 0.4913 1.0000
5.750 1.2956 0.01036 0.00501 -0.1573 0.4757 1.0000
6.000 1.3163 0.01068 0.00528 -0.1561 0.4590 1.0000
6.250 1.3360 0.01103 0.00557 -0.1547 0.4422 1.0000
6.750 1.3702 0.01183 0.00626 -0.1509 0.4041 1.0000
7.000 1.3825 0.01236 0.00669 -0.1482 0.3808 1.0000
7.250 1.3937 0.01297 0.00718 -0.1453 0.3542 1.0000
7.500 1.4042 0.01363 0.00774 -0.1425 0.3281 1.0000
7.750 1.4122 0.01443 0.00840 -0.1393 0.2992 1.0000
8.000 1.4202 0.01528 0.00914 -0.1362 0.2723 1.0000
8.250 1.4278 0.01619 0.00993 -0.1332 0.2472 1.0000
8.500 1.4335 0.01723 0.01084 -0.1301 0.2207 1.0000
8.750 1.4391 0.01835 0.01183 -0.1271 0.1959 1.0000
9.000 1.4466 0.01942 0.01282 -0.1245 0.1748 1.0000
9.500 1.4600 0.02182 0.01506 -0.1195 0.1375 1.0000
9.750 1.4664 0.02312 0.01630 -0.1172 0.1200 1.0000
10.000 1.4721 0.02454 0.01766 -0.1149 0.1035 1.0000
10.250 1.4779 0.02600 0.01907 -0.1128 0.0893 1.0000
10.500 1.4841 0.02749 0.02052 -0.1108 0.0768 1.0000
10.750 1.4908 0.02900 0.02200 -0.1090 0.0661 1.0000
11.000 1.4975 0.03056 0.02355 -0.1073 0.0566 1.0000
11.250 1.5038 0.03220 0.02518 -0.1057 0.0483 1.0000
11.500 1.5093 0.03395 0.02692 -0.1041 0.0409 1.0000
11.750 1.5151 0.03573 0.02870 -0.1026 0.0345 1.0000
12.000 1.5211 0.03755 0.03054 -0.1013 0.0291 1.0000
12.250 1.5260 0.03951 0.03253 -0.0999 0.0245 1.0000
12.500 1.5324 0.04140 0.03446 -0.0988 0.0209 1.0000
12.750 1.5372 0.04348 0.03656 -0.0977 0.0178 1.0000
13.000 1.5436 0.04546 0.03860 -0.0967 0.0157 1.0000
13.250 1.5475 0.04775 0.04093 -0.0957 0.0134 1.0000
13.500 1.5535 0.04988 0.04313 -0.0949 0.0120 1.0000
13.750 1.5580 0.05221 0.04551 -0.0942 0.0103 1.0000
14.000 1.5613 0.05475 0.04811 -0.0935 0.0090 1.0000
14.250 1.5663 0.05714 0.05059 -0.0930 0.0082 1.0000
14.500 1.5701 0.05973 0.05325 -0.0925 0.0072 1.0000
14.750 1.5723 0.06257 0.05615 -0.0921 0.0065 1.0000
15.000 1.5751 0.06541 0.05910 -0.0918 0.0058 1.0000
15.250 1.5778 0.06831 0.06210 -0.0916 0.0053 1.0000
15.500 1.5795 0.07140 0.06528 -0.0915 0.0048 1.0000
15.750 1.5798 0.07475 0.06871 -0.0916 0.0044 1.0000
16.000 1.5795 0.07827 0.07233 -0.0917 0.0040 1.0000
16.250 1.5803 0.08168 0.07584 -0.0920 0.0037 1.0000
16.500 1.5805 0.08524 0.07951 -0.0924 0.0034 1.0000
16.750 1.5799 0.08897 0.08335 -0.0930 0.0032 1.0000
17.000 1.5785 0.09290 0.08737 -0.0936 0.0029 1.0000
17.250 1.5760 0.09705 0.09163 -0.0945 0.0028 1.0000
17.500 1.5715 0.10158 0.09627 -0.0956 0.0026 1.0000
17.750 1.5688 0.10588 0.10068 -0.0967 0.0025 1.0000
18.000 1.5661 0.11025 0.10518 -0.0980 0.0024 1.0000
18.250 1.5625 0.11480 0.10987 -0.0995 0.0023 1.0000
18.500 1.5585 0.11948 0.11468 -0.1012 0.0022 1.0000
18.750 1.5540 0.12429 0.11961 -0.1030 0.0021 1.0000
19.000 1.5491 0.12919 0.12463 -0.1050 0.0020 1.0000
19.250 1.5439 0.13421 0.12977 -0.1072 0.0020 1.0000
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Polar data table (+)
Polar graphs
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