EPPLER E854 AIRFOIL (e854-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER E854 AIRFOIL (e854-il) Reynolds number: 100,000 Max Cl/Cd: 58.15 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e854-il-100000-n5.txt Download as CSV file: xf-e854-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E854 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4051 0.09412 0.08925 -0.0504 1.0000 0.0184
-10.000 -0.4150 0.08849 0.08370 -0.0522 1.0000 0.0180
-9.750 -0.4304 0.08131 0.07660 -0.0549 1.0000 0.0174
-9.500 -0.4841 0.06708 0.06233 -0.0629 1.0000 0.0158
-9.250 -0.5219 0.06092 0.05609 -0.0649 1.0000 0.0154
-9.000 -0.5576 0.05755 0.05263 -0.0635 1.0000 0.0150
-8.750 -0.5803 0.05459 0.04957 -0.0622 1.0000 0.0150
-8.500 -0.5876 0.05057 0.04528 -0.0635 0.9970 0.0151
-8.250 -0.5715 0.04521 0.03944 -0.0689 0.9884 0.0152
-8.000 -0.5490 0.04162 0.03551 -0.0728 0.9811 0.0158
-7.750 -0.5239 0.03899 0.03259 -0.0757 0.9733 0.0168
-7.500 -0.4992 0.03621 0.02941 -0.0778 0.9650 0.0183
-7.250 -0.4695 0.03315 0.02580 -0.0801 0.9589 0.0197
-7.000 -0.4439 0.03063 0.02280 -0.0806 0.9500 0.0207
-6.750 -0.4149 0.02819 0.02018 -0.0820 0.9437 0.0220
-6.500 -0.3862 0.02655 0.01841 -0.0830 0.9358 0.0238
-6.250 -0.3550 0.02525 0.01686 -0.0841 0.9288 0.0282
-6.000 -0.3252 0.02370 0.01531 -0.0853 0.9215 0.0327
-5.750 -0.2949 0.02243 0.01392 -0.0863 0.9139 0.0402
-5.500 -0.2628 0.02126 0.01270 -0.0877 0.9071 0.0516
-5.250 -0.2318 0.02018 0.01159 -0.0889 0.8993 0.0685
-5.000 -0.1977 0.01909 0.01054 -0.0908 0.8925 0.0957
-4.750 -0.1659 0.01803 0.00962 -0.0924 0.8842 0.1403
-4.500 -0.1310 0.01663 0.00873 -0.0950 0.8777 0.2508
-4.250 -0.1003 0.01598 0.00857 -0.0960 0.8686 0.3856
-4.000 -0.0627 0.01587 0.00838 -0.0978 0.8621 0.4488
-3.750 -0.0315 0.01587 0.00828 -0.0982 0.8519 0.4820
-3.500 0.0031 0.01585 0.00809 -0.0994 0.8435 0.5081
-3.250 0.0370 0.01584 0.00794 -0.1003 0.8348 0.5297
-3.000 0.0682 0.01588 0.00784 -0.1007 0.8249 0.5509
-2.750 0.1015 0.01588 0.00774 -0.1015 0.8165 0.5685
-2.500 0.1328 0.01584 0.00755 -0.1020 0.8068 0.5814
-2.250 0.1633 0.01578 0.00738 -0.1025 0.7971 0.5908
-2.000 0.1963 0.01570 0.00716 -0.1035 0.7889 0.5990
-1.750 0.2257 0.01566 0.00700 -0.1038 0.7790 0.6076
-1.500 0.2554 0.01562 0.00688 -0.1042 0.7701 0.6146
-1.250 0.2868 0.01558 0.00670 -0.1049 0.7620 0.6232
-1.000 0.3141 0.01558 0.00667 -0.1048 0.7528 0.6299
-0.750 0.3450 0.01557 0.00654 -0.1055 0.7454 0.6384
-0.500 0.3718 0.01560 0.00655 -0.1052 0.7366 0.6454
-0.250 0.4010 0.01562 0.00649 -0.1056 0.7292 0.6538
0.000 0.4282 0.01566 0.00651 -0.1055 0.7213 0.6616
0.250 0.4563 0.01570 0.00652 -0.1056 0.7142 0.6701
0.500 0.4837 0.01576 0.00657 -0.1055 0.7068 0.6791
0.750 0.5110 0.01582 0.00663 -0.1055 0.7001 0.6879
1.000 0.5378 0.01590 0.00672 -0.1053 0.6930 0.6979
1.250 0.5657 0.01598 0.00679 -0.1053 0.6870 0.7081
1.500 0.5912 0.01608 0.00694 -0.1049 0.6798 0.7186
1.750 0.6198 0.01616 0.00703 -0.1051 0.6744 0.7303
2.000 0.6439 0.01629 0.00725 -0.1045 0.6673 0.7430
2.250 0.6711 0.01638 0.00738 -0.1043 0.6616 0.7569
2.500 0.6956 0.01651 0.00761 -0.1037 0.6553 0.7721
2.750 0.7204 0.01661 0.00781 -0.1031 0.6493 0.7893
3.000 0.7461 0.01670 0.00798 -0.1026 0.6441 0.8097
3.250 0.7675 0.01682 0.00825 -0.1013 0.6375 0.8343
3.500 0.7922 0.01686 0.00842 -0.1005 0.6324 0.8663
3.750 0.8180 0.01694 0.00867 -0.1000 0.6261 0.9189
4.000 0.8514 0.01709 0.00890 -0.1015 0.6200 1.0000
4.250 0.8797 0.01736 0.00921 -0.1019 0.6142 1.0000
4.500 0.9051 0.01766 0.00958 -0.1017 0.6073 1.0000
4.750 0.9341 0.01789 0.00982 -0.1021 0.6013 1.0000
5.000 0.9573 0.01819 0.01023 -0.1014 0.5928 1.0000
5.250 0.9838 0.01840 0.01052 -0.1012 0.5849 1.0000
5.500 1.0086 0.01860 0.01078 -0.1007 0.5753 1.0000
5.750 1.0310 0.01879 0.01107 -0.0997 0.5635 1.0000
6.000 1.0534 0.01893 0.01128 -0.0986 0.5504 1.0000
6.250 1.0752 0.01906 0.01153 -0.0974 0.5363 1.0000
6.500 1.0962 0.01922 0.01178 -0.0960 0.5217 1.0000
6.750 1.1166 0.01941 0.01207 -0.0946 0.5064 1.0000
7.000 1.1362 0.01961 0.01236 -0.0930 0.4897 1.0000
7.250 1.1542 0.01985 0.01269 -0.0912 0.4704 1.0000
7.500 1.1697 0.02014 0.01307 -0.0890 0.4471 1.0000
7.750 1.1834 0.02050 0.01350 -0.0864 0.4180 1.0000
8.000 1.1934 0.02101 0.01394 -0.0833 0.3781 1.0000
8.250 1.1967 0.02178 0.01448 -0.0792 0.3275 1.0000
8.500 1.1932 0.02300 0.01535 -0.0744 0.2752 1.0000
8.750 1.1886 0.02451 0.01658 -0.0699 0.2297 1.0000
9.000 1.1854 0.02612 0.01799 -0.0660 0.1925 1.0000
9.250 1.1826 0.02784 0.01954 -0.0625 0.1623 1.0000
9.500 1.1817 0.02957 0.02118 -0.0596 0.1379 1.0000
9.750 1.1814 0.03139 0.02293 -0.0569 0.1186 1.0000
10.000 1.1820 0.03327 0.02478 -0.0547 0.1025 1.0000
10.250 1.1828 0.03524 0.02675 -0.0527 0.0896 1.0000
10.500 1.1835 0.03733 0.02889 -0.0509 0.0788 1.0000
10.750 1.1832 0.03961 0.03114 -0.0493 0.0696 1.0000
11.000 1.1861 0.04173 0.03335 -0.0480 0.0609 1.0000
11.250 1.1871 0.04410 0.03577 -0.0467 0.0544 1.0000
11.500 1.1885 0.04652 0.03825 -0.0457 0.0483 1.0000
11.750 1.1894 0.04908 0.04088 -0.0447 0.0436 1.0000
12.000 1.1919 0.05154 0.04345 -0.0440 0.0387 1.0000
12.250 1.1906 0.05448 0.04641 -0.0433 0.0352 1.0000
12.500 1.1941 0.05702 0.04913 -0.0426 0.0315 1.0000
12.750 1.1952 0.05984 0.05203 -0.0424 0.0285 1.0000
13.000 1.1940 0.06302 0.05526 -0.0420 0.0263 1.0000
13.250 1.1977 0.06579 0.05824 -0.0416 0.0240 1.0000
13.500 1.1992 0.06883 0.06143 -0.0415 0.0219 1.0000
13.750 1.1984 0.07219 0.06491 -0.0418 0.0204 1.0000
14.000 1.1967 0.07580 0.06861 -0.0421 0.0189 1.0000
14.250 1.1986 0.07914 0.07221 -0.0421 0.0178 1.0000
14.500 1.1989 0.08279 0.07608 -0.0423 0.0169 1.0000
14.750 1.1975 0.08674 0.08024 -0.0429 0.0161 1.0000
15.000 1.1943 0.09099 0.08468 -0.0439 0.0155 1.0000
15.250 1.1900 0.09545 0.08931 -0.0452 0.0150 1.0000
15.500 1.1842 0.10017 0.09416 -0.0469 0.0144 1.0000
15.750 1.1781 0.10509 0.09922 -0.0489 0.0140 1.0000
16.250 1.1594 0.11675 0.11126 -0.0541 0.0134 1.0000
16.500 1.1473 0.12353 0.11829 -0.0577 0.0132 1.0000
16.750 1.1343 0.13082 0.12581 -0.0618 0.0131 1.0000
17.000 1.1197 0.13881 0.13402 -0.0667 0.0131 1.0000
17.250 1.1050 0.14729 0.14269 -0.0721 0.0131 1.0000
17.500 1.0899 0.15635 0.15191 -0.0779 0.0133 1.0000
17.750 1.0754 0.16575 0.16142 -0.0840 0.0135 1.0000
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