EPPLER 858 AIRFOIL (e858-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: EPPLER 858 AIRFOIL (e858-il) Reynolds number: 50,000 Max Cl/Cd: 12.99 at α=2.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e858-il-50000-n5.txt Download as CSV file: xf-e858-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 858 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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.3418 0.11254 0.10553 -0.0595 1.0000 0.0735
-12.750 -0.3707 0.10412 0.09714 -0.0624 1.0000 0.0753
-12.500 -0.4435 0.08912 0.08192 -0.0691 1.0000 0.0754
-12.250 -0.4793 0.08218 0.07485 -0.0710 1.0000 0.0761
-12.000 -0.5079 0.07715 0.06971 -0.0716 1.0000 0.0771
-11.750 -0.5352 0.07305 0.06549 -0.0713 1.0000 0.0782
-11.500 -0.5616 0.06976 0.06209 -0.0701 1.0000 0.0792
-11.250 -0.5382 0.06794 0.06038 -0.0731 0.9932 0.0835
-11.000 -0.5238 0.06404 0.05631 -0.0782 0.9828 0.0885
-10.750 -0.5088 0.06069 0.05281 -0.0824 0.9706 0.0944
-10.500 -0.4889 0.05836 0.05052 -0.0853 0.9572 0.1004
-10.250 -0.4783 0.05569 0.04779 -0.0874 0.9403 0.1069
-10.000 -0.4683 0.05290 0.04488 -0.0897 0.9243 0.1144
-9.750 -0.4536 0.05076 0.04277 -0.0916 0.9094 0.1226
-9.500 -0.4399 0.04854 0.04056 -0.0933 0.8952 0.1318
-9.250 -0.4267 0.04624 0.03825 -0.0951 0.8821 0.1422
-9.000 -0.4211 0.04419 0.03618 -0.0952 0.8660 0.1522
-8.750 -0.4119 0.04227 0.03425 -0.0954 0.8509 0.1642
-8.500 -0.3958 0.04039 0.03241 -0.0962 0.8383 0.1795
-8.250 -0.3771 0.03874 0.03083 -0.0970 0.8257 0.1971
-8.000 -0.3619 0.03753 0.02971 -0.0966 0.8111 0.2158
-7.750 -0.3270 0.03650 0.02876 -0.0988 0.8018 0.2425
-7.500 -0.3072 0.03636 0.02868 -0.0978 0.7864 0.2638
-7.250 -0.2788 0.03601 0.02822 -0.0984 0.7742 0.2892
-7.000 -0.2477 0.03609 0.02818 -0.0987 0.7617 0.3115
-6.750 -0.2237 0.03629 0.02823 -0.0979 0.7483 0.3302
-6.500 -0.1870 0.03651 0.02823 -0.0988 0.7374 0.3493
-6.250 -0.1671 0.03688 0.02846 -0.0971 0.7235 0.3635
-6.000 -0.1228 0.03756 0.02892 -0.0982 0.7135 0.3779
-5.750 -0.1139 0.03735 0.02857 -0.0958 0.7001 0.3906
-5.500 -0.0847 0.03687 0.02774 -0.0968 0.6910 0.4071
-5.250 -0.0635 0.03773 0.02862 -0.0940 0.6780 0.4139
-5.000 -0.0385 0.03695 0.02750 -0.0949 0.6694 0.4294
-4.750 -0.0187 0.03766 0.02823 -0.0921 0.6576 0.4355
-4.500 0.0072 0.03729 0.02759 -0.0923 0.6490 0.4477
-4.250 0.0247 0.03731 0.02752 -0.0905 0.6390 0.4558
-4.000 0.0490 0.03738 0.02747 -0.0895 0.6298 0.4641
-3.750 0.0717 0.03668 0.02649 -0.0899 0.6224 0.4755
-3.500 0.0872 0.03696 0.02678 -0.0874 0.6126 0.4809
-3.250 0.1146 0.03670 0.02633 -0.0874 0.6053 0.4894
-3.000 0.1311 0.03620 0.02562 -0.0868 0.5976 0.4984
-2.750 0.1491 0.03632 0.02572 -0.0849 0.5893 0.5032
-2.500 0.1781 0.03608 0.02530 -0.0852 0.5829 0.5099
-2.250 0.1949 0.03580 0.02486 -0.0845 0.5758 0.5178
-2.000 0.2104 0.03575 0.02474 -0.0830 0.5683 0.5230
-1.750 0.2376 0.03564 0.02451 -0.0828 0.5624 0.5280
-1.500 0.2622 0.03553 0.02425 -0.0826 0.5566 0.5341
-1.250 0.2716 0.03562 0.02429 -0.0805 0.5491 0.5405
-1.000 0.2945 0.03554 0.02409 -0.0802 0.5433 0.5459
-0.750 0.3256 0.03543 0.02385 -0.0807 0.5388 0.5508
-0.500 0.3364 0.03576 0.02418 -0.0784 0.5328 0.5560
-0.250 0.3477 0.03605 0.02442 -0.0765 0.5264 0.5620
0.000 0.3725 0.03603 0.02426 -0.0766 0.5214 0.5681
0.250 0.4053 0.03595 0.02404 -0.0773 0.5174 0.5731
0.500 0.4092 0.03659 0.02474 -0.0742 0.5115 0.5779
0.750 0.4143 0.03723 0.02539 -0.0714 0.5057 0.5835
1.000 0.4354 0.03749 0.02554 -0.0710 0.5013 0.5903
1.250 0.4647 0.03754 0.02551 -0.0712 0.4978 0.5957
1.500 0.4899 0.03777 0.02566 -0.0711 0.4942 0.6017
1.750 0.4574 0.03955 0.02762 -0.0633 0.4871 0.6058
2.000 0.4653 0.04039 0.02840 -0.0614 0.4821 0.6123
2.250 0.4902 0.04061 0.02859 -0.0611 0.4787 0.6182
2.500 0.5265 0.04054 0.02840 -0.0623 0.4761 0.6261
2.750 0.4725 0.04436 0.03245 -0.0538 0.4684 0.6292
3.000 0.4521 0.04726 0.03539 -0.0502 0.4616 0.6346
3.250 0.4736 0.04772 0.03584 -0.0496 0.4584 0.6411
3.500 0.5069 0.04755 0.03559 -0.0501 0.4562 0.6499
3.750 0.5471 0.04711 0.03504 -0.0514 0.4545 0.6600
4.250 0.4453 0.05894 0.04725 -0.0434 0.4363 0.6660
4.500 0.4758 0.05884 0.04707 -0.0434 0.4348 0.6773
6.000 0.4174 0.08141 0.07014 -0.0410 0.4005 0.7272
6.250 0.4358 0.08257 0.07136 -0.0408 0.3984 0.7448
6.500 0.4581 0.08327 0.07215 -0.0406 0.3967 0.7672
6.750 0.4291 0.08890 0.07797 -0.0406 0.3900 0.7801
7.250 0.4438 0.09295 0.08246 -0.0414 0.3827 1.0000
7.500 0.4633 0.09479 0.08418 -0.0425 0.3804 1.0000
7.750 0.4871 0.09614 0.08539 -0.0433 0.3785 1.0000
8.000 0.4813 0.10001 0.08923 -0.0440 0.3741 1.0000
8.250 0.4757 0.10372 0.09294 -0.0447 0.3694 1.0000
8.500 0.4835 0.10639 0.09557 -0.0454 0.3665 1.0000
8.750 0.4965 0.10860 0.09771 -0.0460 0.3640 1.0000
9.000 0.5153 0.11025 0.09929 -0.0464 0.3617 1.0000
9.250 0.5389 0.11150 0.10046 -0.0467 0.3598 1.0000
9.500 0.5254 0.11580 0.10479 -0.0475 0.3550 1.0000
9.750 0.5246 0.11904 0.10804 -0.0482 0.3518 1.0000
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Polar data table (+)
Polar graphs
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