EPPLER E851 AIRFOIL (e851-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER E851 AIRFOIL (e851-il) Reynolds number: 1,000,000 Max Cl/Cd: 95.68 at α=1.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e851-il-1000000-n5.txt Download as CSV file: xf-e851-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER E851 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4630 0.11370 0.11201 -0.0297 1.0000 0.0030
-10.500 -0.4675 0.10880 0.10712 -0.0309 1.0000 0.0031
-10.250 -0.4700 0.10466 0.10301 -0.0318 1.0000 0.0032
-10.000 -0.4697 0.10030 0.09867 -0.0337 0.9998 0.0033
-9.750 -0.4629 0.09533 0.09370 -0.0372 0.9991 0.0032
-9.500 -0.4582 0.09014 0.08851 -0.0413 0.9982 0.0033
-9.250 -0.4531 0.08494 0.08332 -0.0457 0.9970 0.0034
-9.000 -0.3622 0.06452 0.06299 -0.0587 0.9918 0.0035
-8.750 -0.3666 0.05768 0.05616 -0.0628 0.9894 0.0034
-8.500 -0.3689 0.05092 0.04941 -0.0685 0.9865 0.0036
-8.250 -0.3833 0.03946 0.03784 -0.0816 0.9823 0.0034
-8.000 -0.3940 0.03423 0.03246 -0.0876 0.9711 0.0034
-7.750 -0.3939 0.02848 0.02651 -0.0910 0.9624 0.0034
-7.500 -0.3822 0.02297 0.02073 -0.0947 0.9572 0.0035
-7.250 -0.3683 0.01809 0.01554 -0.0968 0.9501 0.0035
-7.000 -0.3455 0.01483 0.01200 -0.0980 0.9448 0.0031
-6.750 -0.3229 0.01306 0.01007 -0.0991 0.9385 0.0026
-6.500 -0.3232 0.02072 0.01709 -0.1015 0.9414 0.0023
-6.250 -0.2991 0.01667 0.01252 -0.1017 0.9342 0.0019
-6.000 -0.2729 0.01378 0.00923 -0.1017 0.9282 0.0017
-5.750 -0.2479 0.01186 0.00701 -0.1013 0.9212 0.0015
-5.500 -0.2224 0.01048 0.00539 -0.1009 0.9151 0.0014
-5.250 -0.1970 0.00956 0.00429 -0.1006 0.9090 0.0014
-5.000 -0.1700 0.00894 0.00346 -0.1006 0.9040 0.0013
-4.750 -0.1435 0.00851 0.00291 -0.1004 0.8987 0.0014
-4.500 -0.1161 0.00820 0.00250 -0.1005 0.8938 0.0014
-4.250 -0.0885 0.00796 0.00216 -0.1005 0.8897 0.0015
-4.000 -0.0611 0.00776 0.00191 -0.1005 0.8853 0.0018
-3.750 -0.0335 0.00762 0.00172 -0.1006 0.8811 0.0026
-3.500 -0.0060 0.00738 0.00153 -0.1007 0.8774 0.0168
-3.250 0.0212 0.00715 0.00138 -0.1008 0.8735 0.0401
-3.000 0.0485 0.00692 0.00122 -0.1009 0.8697 0.0722
-2.750 0.0730 0.00581 0.00092 -0.1012 0.8658 0.3126
-2.500 0.0997 0.00545 0.00085 -0.1014 0.8623 0.4054
-2.250 0.1275 0.00535 0.00081 -0.1015 0.8587 0.4359
-2.000 0.1554 0.00529 0.00078 -0.1017 0.8553 0.4589
-1.750 0.1833 0.00523 0.00077 -0.1018 0.8522 0.4834
-1.500 0.2112 0.00519 0.00074 -0.1019 0.8489 0.5036
-1.250 0.2391 0.00515 0.00074 -0.1020 0.8452 0.5191
-1.000 0.2671 0.00514 0.00073 -0.1021 0.8413 0.5300
-0.750 0.2949 0.00513 0.00072 -0.1022 0.8369 0.5378
-0.500 0.3226 0.00512 0.00072 -0.1022 0.8308 0.5447
-0.250 0.3501 0.00513 0.00073 -0.1022 0.8243 0.5516
0.000 0.3774 0.00513 0.00074 -0.1021 0.8163 0.5585
0.250 0.4046 0.00514 0.00075 -0.1020 0.8073 0.5656
0.500 0.4315 0.00516 0.00076 -0.1019 0.7968 0.5727
0.750 0.4583 0.00518 0.00079 -0.1017 0.7848 0.5803
1.000 0.4844 0.00522 0.00081 -0.1013 0.7661 0.5878
1.250 0.5090 0.00532 0.00087 -0.1006 0.7351 0.5960
1.500 0.5307 0.00557 0.00093 -0.0993 0.6782 0.6039
1.750 0.5494 0.00604 0.00108 -0.0974 0.5917 0.6121
2.000 0.5680 0.00663 0.00131 -0.0957 0.4970 0.6213
2.250 0.5877 0.00720 0.00155 -0.0943 0.4048 0.6308
2.500 0.6033 0.00815 0.00190 -0.0922 0.2559 0.6405
2.750 0.6240 0.00874 0.00221 -0.0911 0.1697 0.6513
3.000 0.6434 0.00947 0.00255 -0.0897 0.0710 0.6625
3.250 0.6655 0.00999 0.00285 -0.0888 0.0197 0.6749
3.500 0.6908 0.01018 0.00306 -0.0884 0.0126 0.6886
3.750 0.7148 0.01051 0.00336 -0.0877 0.0018 0.7033
4.000 0.7401 0.01069 0.00362 -0.0873 0.0013 0.7197
4.250 0.7650 0.01092 0.00394 -0.0868 0.0010 0.7375
4.500 0.7894 0.01120 0.00432 -0.0862 0.0009 0.7570
4.750 0.8133 0.01151 0.00477 -0.0854 0.0008 0.7796
5.000 0.8363 0.01189 0.00530 -0.0844 0.0008 0.8054
5.250 0.8580 0.01236 0.00602 -0.0832 0.0008 0.8370
5.500 0.8776 0.01286 0.00674 -0.0814 0.0008 0.8816
5.750 0.8965 0.01348 0.00765 -0.0793 0.0008 1.0000
6.000 0.9168 0.01453 0.00885 -0.0778 0.0008 1.0000
6.250 0.9366 0.01601 0.01053 -0.0761 0.0008 1.0000
6.500 0.9572 0.01817 0.01295 -0.0744 0.0009 1.0000
6.750 0.9781 0.02125 0.01640 -0.0726 0.0010 1.0000
7.000 0.9948 0.02535 0.02098 -0.0699 0.0012 1.0000
7.250 1.0049 0.03007 0.02618 -0.0663 0.0014 1.0000
7.500 1.0081 0.03543 0.03202 -0.0619 0.0015 1.0000
12.000 0.8469 0.13389 0.13247 -0.0656 0.0022 1.0000
12.250 0.8454 0.14022 0.13878 -0.0686 0.0023 1.0000
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Polar data table (+)
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