EPPLER E852 AIRFOIL (e852-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER E852 AIRFOIL (e852-il) Reynolds number: 200,000 Max Cl/Cd: 84.21 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e852-il-200000.txt Download as CSV file: xf-e852-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E852 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4308 0.08958 0.08625 -0.0446 1.0000 0.0411
-8.500 -0.4459 0.08552 0.08229 -0.0475 1.0000 0.0421
-8.250 -0.4649 0.08184 0.07877 -0.0485 1.0000 0.0422
-8.000 -0.4820 0.07949 0.07651 -0.0462 1.0000 0.0420
-7.750 -0.4999 0.07772 0.07482 -0.0427 1.0000 0.0417
-7.000 -0.5021 0.06277 0.05915 -0.0616 0.9869 0.0430
-6.750 -0.4899 0.05537 0.05192 -0.0639 0.9843 0.0459
-6.500 -0.4658 0.05113 0.04753 -0.0682 0.9803 0.0487
-5.500 -0.3570 0.02934 0.02350 -0.0784 0.9609 0.0273
-5.250 -0.3233 0.02506 0.01855 -0.0796 0.9586 0.0234
-5.000 -0.2873 0.02218 0.01517 -0.0808 0.9569 0.0218
-4.750 -0.2603 0.02044 0.01321 -0.0806 0.9523 0.0219
-4.500 -0.2298 0.01887 0.01153 -0.0812 0.9486 0.0237
-4.250 -0.1956 0.01754 0.01010 -0.0825 0.9461 0.0285
-4.000 -0.1592 0.01606 0.00866 -0.0848 0.9441 0.0593
-3.750 -0.1319 0.01434 0.00757 -0.0858 0.9396 0.1870
-3.500 -0.1034 0.01322 0.00746 -0.0870 0.9358 0.4749
-3.250 -0.0690 0.01323 0.00745 -0.0883 0.9329 0.5361
-3.000 -0.0323 0.01323 0.00740 -0.0900 0.9309 0.5702
-2.750 -0.0086 0.01335 0.00746 -0.0892 0.9249 0.5947
-2.500 0.0237 0.01335 0.00741 -0.0901 0.9215 0.6152
-2.250 0.0589 0.01333 0.00736 -0.0915 0.9192 0.6368
-2.000 0.0962 0.01329 0.00726 -0.0932 0.9176 0.6605
-1.750 0.1172 0.01339 0.00736 -0.0920 0.9111 0.6745
-1.500 0.1510 0.01332 0.00725 -0.0933 0.9082 0.6870
-1.250 0.1883 0.01319 0.00709 -0.0953 0.9063 0.6986
-1.000 0.2260 0.01304 0.00692 -0.0974 0.9046 0.7096
-0.750 0.2479 0.01315 0.00705 -0.0964 0.8985 0.7203
-0.500 0.2799 0.01309 0.00700 -0.0974 0.8951 0.7321
-0.250 0.3153 0.01296 0.00690 -0.0989 0.8928 0.7446
0.000 0.3517 0.01282 0.00680 -0.1007 0.8910 0.7579
0.250 0.3704 0.01299 0.00704 -0.0991 0.8838 0.7719
0.500 0.4027 0.01289 0.00700 -0.0999 0.8806 0.7873
0.750 0.4377 0.01273 0.00691 -0.1013 0.8782 0.8045
1.000 0.4571 0.01285 0.00714 -0.0997 0.8713 0.8235
1.250 0.4865 0.01272 0.00714 -0.0998 0.8673 0.8456
1.500 0.5184 0.01250 0.00703 -0.1002 0.8645 0.8714
1.750 0.5342 0.01256 0.00723 -0.0975 0.8565 0.9104
2.000 0.5799 0.01224 0.00703 -0.1009 0.8530 0.9661
2.250 0.6166 0.01219 0.00706 -0.1031 0.8463 1.0000
2.500 0.6525 0.01200 0.00689 -0.1045 0.8395 1.0000
2.750 0.6817 0.01191 0.00683 -0.1046 0.8295 1.0000
3.000 0.7135 0.01162 0.00656 -0.1047 0.8173 1.0000
3.250 0.7442 0.01128 0.00624 -0.1045 0.8022 1.0000
3.500 0.7728 0.01109 0.00614 -0.1040 0.7878 1.0000
3.750 0.8006 0.01095 0.00605 -0.1035 0.7729 1.0000
4.000 0.8256 0.01082 0.00598 -0.1023 0.7537 1.0000
4.250 0.8506 0.01067 0.00587 -0.1011 0.7304 1.0000
4.500 0.8718 0.01060 0.00585 -0.0991 0.6980 1.0000
4.750 0.8918 0.01059 0.00581 -0.0969 0.6477 1.0000
5.000 0.9053 0.01101 0.00578 -0.0933 0.5343 1.0000
5.250 0.9002 0.01274 0.00642 -0.0872 0.3480 1.0000
5.500 0.8971 0.01484 0.00748 -0.0822 0.1748 1.0000
5.750 0.9032 0.01660 0.00863 -0.0788 0.0878 1.0000
6.000 0.9136 0.01819 0.00984 -0.0760 0.0354 1.0000
6.250 0.9230 0.01999 0.01167 -0.0728 0.0175 1.0000
6.500 0.9382 0.02137 0.01318 -0.0704 0.0143 1.0000
6.750 0.9553 0.02291 0.01482 -0.0685 0.0130 1.0000
7.000 0.9760 0.02473 0.01675 -0.0672 0.0121 1.0000
7.250 1.0017 0.02706 0.01925 -0.0666 0.0117 1.0000
7.500 1.0302 0.02993 0.02242 -0.0664 0.0118 1.0000
7.750 1.0567 0.03366 0.02660 -0.0655 0.0124 1.0000
8.000 1.0747 0.03841 0.03197 -0.0632 0.0137 1.0000
8.250 1.0842 0.04307 0.03714 -0.0602 0.0151 1.0000
8.500 1.0869 0.04765 0.04213 -0.0569 0.0163 1.0000
8.750 1.0817 0.05294 0.04777 -0.0535 0.0176 1.0000
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Polar data table (+)
Polar graphs
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