EPPLER E851 AIRFOIL (e851-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER E851 AIRFOIL (e851-il) Reynolds number: 500,000 Max Cl/Cd: 90.54 at α=2.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e851-il-500000-n5.txt Download as CSV file: xf-e851-il-500000-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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4462 0.11004 0.10766 -0.0331 1.0000 0.0077
-10.000 -0.4458 0.10634 0.10399 -0.0338 1.0000 0.0077
-8.500 -0.4552 0.07922 0.07703 -0.0455 0.9967 0.0065
-8.250 -0.4516 0.07207 0.06990 -0.0535 0.9936 0.0055
-8.000 -0.4490 0.06349 0.06132 -0.0648 0.9870 0.0055
-7.750 -0.4415 0.05416 0.05180 -0.0788 0.9799 0.0052
-7.500 -0.4405 0.04173 0.03893 -0.0853 0.9702 0.0032
-7.250 -0.4213 0.03877 0.03578 -0.0866 0.9651 0.0030
-7.000 -0.4044 0.03526 0.03203 -0.0885 0.9596 0.0027
-6.750 -0.3851 0.02922 0.02551 -0.0910 0.9563 0.0025
-6.500 -0.3670 0.02511 0.02096 -0.0911 0.9500 0.0024
-6.250 -0.3414 0.02125 0.01660 -0.0920 0.9466 0.0023
-6.000 -0.3121 0.01820 0.01311 -0.0930 0.9444 0.0022
-5.750 -0.2836 0.01601 0.01057 -0.0935 0.9418 0.0021
-5.500 -0.2577 0.01430 0.00861 -0.0933 0.9373 0.0021
-5.250 -0.2285 0.01287 0.00697 -0.0939 0.9342 0.0021
-5.000 -0.1979 0.01171 0.00557 -0.0947 0.9316 0.0021
-4.750 -0.1684 0.01088 0.00458 -0.0953 0.9283 0.0022
-4.500 -0.1401 0.01030 0.00384 -0.0956 0.9241 0.0023
-4.250 -0.1096 0.00986 0.00324 -0.0963 0.9208 0.0026
-4.000 -0.0782 0.00950 0.00277 -0.0971 0.9180 0.0047
-3.750 -0.0504 0.00904 0.00246 -0.0975 0.9139 0.0342
-3.500 -0.0236 0.00827 0.00214 -0.0980 0.9097 0.1450
-3.250 0.0046 0.00757 0.00185 -0.0988 0.9062 0.2698
-3.000 0.0323 0.00698 0.00170 -0.0994 0.9028 0.4095
-2.750 0.0595 0.00682 0.00162 -0.0994 0.8987 0.4595
-2.500 0.0882 0.00675 0.00155 -0.0997 0.8951 0.4822
-2.250 0.1177 0.00669 0.00150 -0.1002 0.8920 0.5049
-2.000 0.1456 0.00664 0.00148 -0.1003 0.8884 0.5286
-1.750 0.1732 0.00660 0.00147 -0.1003 0.8845 0.5458
-1.250 0.2311 0.00656 0.00138 -0.1009 0.8782 0.5654
-1.000 0.2585 0.00655 0.00138 -0.1009 0.8744 0.5731
-0.750 0.2862 0.00654 0.00138 -0.1010 0.8705 0.5809
-0.500 0.3148 0.00653 0.00138 -0.1012 0.8670 0.5885
-0.250 0.3431 0.00653 0.00140 -0.1014 0.8631 0.5968
0.000 0.3701 0.00652 0.00143 -0.1013 0.8578 0.6047
0.250 0.3985 0.00651 0.00143 -0.1014 0.8526 0.6133
0.500 0.4252 0.00651 0.00147 -0.1012 0.8455 0.6223
0.750 0.4531 0.00650 0.00149 -0.1012 0.8380 0.6314
1.000 0.4795 0.00649 0.00152 -0.1008 0.8278 0.6411
1.250 0.5059 0.00649 0.00160 -0.1005 0.8162 0.6514
1.500 0.5320 0.00650 0.00162 -0.1000 0.8010 0.6625
1.750 0.5568 0.00651 0.00165 -0.0993 0.7773 0.6741
2.000 0.5812 0.00657 0.00168 -0.0984 0.7470 0.6862
2.250 0.6048 0.00668 0.00174 -0.0974 0.7084 0.6994
2.500 0.6233 0.00704 0.00185 -0.0953 0.6305 0.7136
2.750 0.6316 0.00809 0.00227 -0.0914 0.4728 0.7287
3.000 0.6421 0.00928 0.00275 -0.0884 0.3013 0.7455
3.250 0.6598 0.01003 0.00313 -0.0867 0.1991 0.7646
3.500 0.6801 0.01057 0.00347 -0.0855 0.1332 0.7861
3.750 0.6984 0.01127 0.00388 -0.0839 0.0584 0.8113
4.000 0.7177 0.01177 0.00426 -0.0823 0.0199 0.8424
4.250 0.7360 0.01212 0.00464 -0.0803 0.0042 0.8866
4.500 0.7607 0.01245 0.00513 -0.0795 0.0019 1.0000
4.750 0.7845 0.01291 0.00569 -0.0788 0.0017 1.0000
5.000 0.8073 0.01350 0.00639 -0.0778 0.0015 1.0000
5.250 0.8289 0.01425 0.00735 -0.0765 0.0014 1.0000
5.500 0.8497 0.01515 0.00837 -0.0752 0.0013 1.0000
5.750 0.8697 0.01629 0.00966 -0.0736 0.0013 1.0000
6.000 0.8903 0.01761 0.01115 -0.0721 0.0013 1.0000
6.250 0.9119 0.01926 0.01299 -0.0709 0.0013 1.0000
6.500 0.9345 0.02130 0.01529 -0.0697 0.0013 1.0000
6.750 0.9565 0.02374 0.01806 -0.0684 0.0014 1.0000
7.000 0.9755 0.02677 0.02148 -0.0665 0.0014 1.0000
7.250 0.9903 0.03028 0.02544 -0.0640 0.0015 1.0000
7.500 1.0003 0.03427 0.02986 -0.0608 0.0015 1.0000
7.750 1.0047 0.03888 0.03491 -0.0571 0.0016 1.0000
8.000 1.0051 0.04373 0.04014 -0.0532 0.0016 1.0000
8.250 1.0009 0.04872 0.04546 -0.0491 0.0017 1.0000
8.500 0.9923 0.05356 0.05058 -0.0452 0.0017 1.0000
8.750 0.9790 0.05800 0.05523 -0.0412 0.0018 1.0000
9.000 0.9583 0.06049 0.05787 -0.0366 0.0019 1.0000
9.250 0.9464 0.06374 0.06125 -0.0337 0.0019 1.0000
9.500 0.9339 0.06730 0.06493 -0.0318 0.0020 1.0000
9.750 0.9192 0.07145 0.06921 -0.0310 0.0020 1.0000
10.000 0.9031 0.07641 0.07428 -0.0315 0.0020 1.0000
10.250 0.8829 0.08308 0.08106 -0.0343 0.0020 1.0000
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Polar data table (+)
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