EPPLER 856 AIRFOIL (e856-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 856 AIRFOIL (e856-il) Reynolds number: 50,000 Max Cl/Cd: 18.81 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e856-il-50000-n5.txt Download as CSV file: xf-e856-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 856 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
------ -------- --------- --------- -------- -------- --------
-11.500 -0.4019 0.09518 0.08837 -0.0662 1.0000 0.0497
-11.250 -0.4257 0.08854 0.08176 -0.0686 1.0000 0.0495
-11.000 -0.4521 0.08246 0.07569 -0.0707 1.0000 0.0491
-10.750 -0.4784 0.07735 0.07058 -0.0718 1.0000 0.0487
-10.500 -0.5088 0.07280 0.06603 -0.0723 1.0000 0.0484
-10.250 -0.5389 0.06931 0.06253 -0.0715 1.0000 0.0481
-10.000 -0.5699 0.06672 0.05994 -0.0694 1.0000 0.0477
-9.750 -0.6008 0.06454 0.05777 -0.0672 0.9988 0.0475
-9.500 -0.6020 0.05916 0.05191 -0.0733 0.9853 0.0485
-9.250 -0.5917 0.05487 0.04718 -0.0774 0.9730 0.0504
-9.000 -0.5700 0.05240 0.04461 -0.0799 0.9617 0.0533
-8.750 -0.5516 0.04922 0.04103 -0.0819 0.9496 0.0563
-8.500 -0.5302 0.04675 0.03836 -0.0833 0.9377 0.0600
-8.250 -0.5071 0.04468 0.03608 -0.0845 0.9261 0.0649
-8.000 -0.4812 0.04271 0.03397 -0.0856 0.9155 0.0704
-7.750 -0.4512 0.04076 0.03176 -0.0872 0.9065 0.0787
-7.500 -0.4286 0.03929 0.03028 -0.0875 0.8944 0.0868
-7.250 -0.4032 0.03774 0.02868 -0.0883 0.8841 0.0973
-7.000 -0.3748 0.03609 0.02697 -0.0895 0.8751 0.1109
-6.750 -0.3535 0.03466 0.02553 -0.0896 0.8634 0.1257
-6.500 -0.3214 0.03286 0.02372 -0.0916 0.8567 0.1488
-6.250 -0.3029 0.03148 0.02247 -0.0915 0.8442 0.1726
-6.000 -0.2784 0.02998 0.02115 -0.0924 0.8343 0.2113
-5.750 -0.2497 0.02883 0.02046 -0.0935 0.8256 0.2724
-5.500 -0.2242 0.02878 0.02063 -0.0930 0.8147 0.3331
-5.250 -0.1864 0.02897 0.02065 -0.0942 0.8073 0.3861
-5.000 -0.1617 0.02935 0.02087 -0.0932 0.7957 0.4169
-4.750 -0.1232 0.02956 0.02082 -0.0942 0.7891 0.4462
-4.500 -0.1016 0.02992 0.02102 -0.0927 0.7773 0.4656
-4.250 -0.0683 0.03010 0.02099 -0.0928 0.7697 0.4861
-4.000 -0.0439 0.03030 0.02104 -0.0917 0.7594 0.5029
-3.750 -0.0145 0.03037 0.02092 -0.0915 0.7511 0.5192
-3.500 0.0114 0.03037 0.02075 -0.0909 0.7419 0.5337
-3.250 0.0399 0.03023 0.02038 -0.0912 0.7338 0.5479
-3.000 0.0649 0.03027 0.02031 -0.0902 0.7249 0.5572
-2.750 0.0947 0.03004 0.01986 -0.0908 0.7176 0.5679
-2.500 0.1176 0.03001 0.01969 -0.0901 0.7086 0.5763
-2.250 0.1529 0.02968 0.01913 -0.0915 0.7029 0.5855
-2.000 0.1693 0.02981 0.01919 -0.0899 0.6931 0.5925
-1.750 0.2038 0.02952 0.01867 -0.0914 0.6873 0.6016
-1.500 0.2213 0.02969 0.01879 -0.0899 0.6786 0.6079
-1.250 0.2519 0.02954 0.01844 -0.0909 0.6723 0.6170
-1.000 0.2766 0.02959 0.01841 -0.0904 0.6658 0.6232
-0.750 0.2976 0.02973 0.01846 -0.0898 0.6582 0.6309
-0.500 0.3308 0.02960 0.01818 -0.0908 0.6533 0.6386
-0.250 0.3464 0.02995 0.01851 -0.0892 0.6456 0.6457
0.000 0.3726 0.03005 0.01850 -0.0894 0.6396 0.6539
0.250 0.4065 0.02996 0.01830 -0.0904 0.6354 0.6617
0.500 0.4171 0.03055 0.01888 -0.0884 0.6274 0.6701
0.750 0.4423 0.03070 0.01899 -0.0881 0.6221 0.6776
1.000 0.4775 0.03064 0.01880 -0.0895 0.6183 0.6876
1.250 0.4816 0.03147 0.01973 -0.0863 0.6105 0.6950
1.500 0.5064 0.03173 0.01994 -0.0863 0.6055 0.7052
1.750 0.5390 0.03170 0.01986 -0.0870 0.6018 0.7151
2.000 0.5419 0.03270 0.02094 -0.0839 0.5945 0.7250
2.250 0.5609 0.03317 0.02142 -0.0830 0.5893 0.7366
2.500 0.5905 0.03325 0.02150 -0.0832 0.5858 0.7489
2.750 0.5975 0.03417 0.02250 -0.0807 0.5798 0.7617
3.000 0.6033 0.03513 0.02356 -0.0781 0.5735 0.7763
3.250 0.6292 0.03529 0.02375 -0.0778 0.5698 0.7940
3.500 0.6618 0.03519 0.02370 -0.0783 0.5672 0.8153
3.750 0.6262 0.03781 0.02656 -0.0708 0.5574 0.8398
4.000 0.6531 0.03804 0.02692 -0.0709 0.5536 0.8833
4.250 0.7013 0.03787 0.02675 -0.0746 0.5510 1.0000
4.750 0.6907 0.04250 0.03134 -0.0701 0.5366 1.0000
5.000 0.7270 0.04263 0.03138 -0.0716 0.5342 1.0000
5.500 0.7095 0.04844 0.03717 -0.0674 0.5189 1.0000
5.750 0.7428 0.04858 0.03727 -0.0681 0.5169 1.0000
6.250 0.7262 0.05527 0.04400 -0.0654 0.5011 1.0000
6.750 0.7154 0.06192 0.05068 -0.0639 0.4863 1.0000
7.000 0.7439 0.06233 0.05108 -0.0640 0.4839 1.0000
7.250 0.7141 0.06779 0.05659 -0.0628 0.4732 1.0000
7.500 0.7359 0.06879 0.05761 -0.0628 0.4696 1.0000
7.750 0.7638 0.06925 0.05809 -0.0628 0.4671 1.0000
8.750 0.7614 0.08117 0.07019 -0.0614 0.4397 1.0000
9.000 0.7836 0.08213 0.07119 -0.0612 0.4360 1.0000
9.500 0.7882 0.08765 0.07683 -0.0609 0.4224 1.0000
9.750 0.8129 0.08833 0.07758 -0.0608 0.4189 1.0000
10.000 0.8016 0.09240 0.08171 -0.0607 0.4096 1.0000
10.250 0.8186 0.09376 0.08315 -0.0606 0.4046 1.0000
10.500 0.8472 0.09398 0.08345 -0.0603 0.4016 1.0000
10.750 0.8293 0.09876 0.08830 -0.0606 0.3906 1.0000
11.000 0.8537 0.09932 0.08895 -0.0603 0.3868 1.0000
11.250 0.8439 0.10336 0.09306 -0.0606 0.3768 1.0000
11.500 0.8640 0.10430 0.09410 -0.0604 0.3720 1.0000
11.750 0.8616 0.10761 0.09749 -0.0607 0.3631 1.0000
12.000 0.8776 0.10888 0.09887 -0.0605 0.3570 1.0000
12.500 0.8925 0.11331 0.10349 -0.0608 0.3419 1.0000
12.750 0.9181 0.11337 0.10367 -0.0602 0.3380 1.0000
13.000 0.9085 0.11758 0.10796 -0.0610 0.3266 1.0000
13.500 0.9251 0.12171 0.11230 -0.0614 0.3111 1.0000
14.000 0.9427 0.12565 0.11644 -0.0618 0.2954 1.0000
14.250 0.9415 0.12904 0.11994 -0.0627 0.2857 1.0000
14.500 0.9616 0.12926 0.12029 -0.0622 0.2797 1.0000
14.750 0.9565 0.13336 0.12447 -0.0636 0.2692 1.0000
15.000 0.9806 0.13284 0.12408 -0.0628 0.2640 1.0000
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Polar data table (+)
Polar graphs
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