EPPLER E851 AIRFOIL (e851-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: EPPLER E851 AIRFOIL (e851-il) Reynolds number: 1,000,000 Max Cl/Cd: 122.75 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-e851-il-1000000.txt Download as CSV file: xf-e851-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.4662 0.09767 0.09607 -0.0327 1.0000 0.0056
-9.250 -0.4692 0.09407 0.09249 -0.0332 1.0000 0.0059
-9.000 -0.4744 0.09059 0.08903 -0.0334 1.0000 0.0059
-8.750 -0.4752 0.08623 0.08470 -0.0355 0.9995 0.0059
-8.500 -0.4655 0.08056 0.07903 -0.0414 0.9980 0.0063
-8.250 -0.4569 0.07398 0.07246 -0.0489 0.9959 0.0062
-8.000 -0.4474 0.06513 0.06361 -0.0614 0.9930 0.0062
-7.750 -0.3779 0.04143 0.03985 -0.0786 0.9843 0.0068
-7.500 -0.3667 0.03514 0.03338 -0.0864 0.9818 0.0071
-7.250 -0.3515 0.03215 0.03026 -0.0882 0.9765 0.0076
-7.000 -0.3361 0.02772 0.02561 -0.0914 0.9726 0.0077
-6.750 -0.3169 0.02308 0.02071 -0.0947 0.9703 0.0078
-6.500 -0.2945 0.01892 0.01625 -0.0976 0.9687 0.0078
-6.250 -0.2799 0.01580 0.01286 -0.0975 0.9615 0.0078
-5.250 -0.2053 0.01174 0.00701 -0.1000 0.9509 0.0042
-5.000 -0.1764 0.01050 0.00555 -0.1002 0.9471 0.0033
-4.750 -0.1447 0.00978 0.00474 -0.1011 0.9444 0.0031
-4.500 -0.1166 0.00905 0.00388 -0.1013 0.9399 0.0029
-4.250 -0.0889 0.00828 0.00294 -0.1014 0.9349 0.0030
-4.000 -0.0583 0.00776 0.00219 -0.1020 0.9313 0.0036
-3.750 -0.0304 0.00737 0.00183 -0.1021 0.9266 0.0261
-3.500 -0.0033 0.00692 0.00162 -0.1023 0.9220 0.0887
-3.250 0.0245 0.00626 0.00137 -0.1029 0.9181 0.2133
-3.000 0.0502 0.00564 0.00116 -0.1031 0.9135 0.3506
-2.750 0.0765 0.00521 0.00115 -0.1032 0.9090 0.4816
-2.500 0.1055 0.00517 0.00111 -0.1035 0.9055 0.5048
-2.250 0.1337 0.00514 0.00108 -0.1037 0.9018 0.5186
-2.000 0.1614 0.00512 0.00106 -0.1038 0.8978 0.5315
-1.750 0.1896 0.00509 0.00105 -0.1039 0.8941 0.5466
-1.500 0.2186 0.00508 0.00102 -0.1042 0.8908 0.5607
-1.250 0.2459 0.00506 0.00103 -0.1042 0.8867 0.5729
-1.000 0.2737 0.00505 0.00102 -0.1043 0.8825 0.5830
-0.750 0.3023 0.00505 0.00101 -0.1045 0.8783 0.5914
-0.500 0.3294 0.00503 0.00102 -0.1044 0.8729 0.5996
-0.250 0.3571 0.00502 0.00101 -0.1043 0.8672 0.6082
0.000 0.3844 0.00501 0.00103 -0.1043 0.8611 0.6169
0.250 0.4117 0.00500 0.00102 -0.1042 0.8540 0.6260
0.500 0.4388 0.00499 0.00104 -0.1040 0.8465 0.6360
0.750 0.4661 0.00499 0.00105 -0.1039 0.8390 0.6463
1.000 0.4924 0.00497 0.00110 -0.1035 0.8286 0.6572
1.250 0.5186 0.00496 0.00112 -0.1032 0.8163 0.6689
1.500 0.5449 0.00496 0.00115 -0.1028 0.8034 0.6815
1.750 0.5714 0.00496 0.00120 -0.1025 0.7912 0.6952
2.000 0.5974 0.00498 0.00125 -0.1021 0.7758 0.7102
2.250 0.6211 0.00506 0.00129 -0.1011 0.7411 0.7266
2.500 0.6392 0.00541 0.00142 -0.0989 0.6588 0.7441
2.750 0.6472 0.00651 0.00179 -0.0950 0.4785 0.7635
3.000 0.6536 0.00806 0.00234 -0.0913 0.2359 0.7853
3.250 0.6692 0.00900 0.00275 -0.0892 0.1012 0.8111
3.500 0.6908 0.00935 0.00302 -0.0881 0.0592 0.8425
3.750 0.7103 0.00972 0.00332 -0.0864 0.0208 0.8849
4.000 0.7320 0.00999 0.00364 -0.0850 0.0036 1.0000
4.250 0.7559 0.01048 0.00429 -0.0841 0.0021 1.0000
4.500 0.7776 0.01124 0.00521 -0.0827 0.0020 1.0000
4.750 0.7982 0.01213 0.00624 -0.0811 0.0020 1.0000
5.000 0.8194 0.01301 0.00721 -0.0797 0.0020 1.0000
5.250 0.8413 0.01388 0.00822 -0.0784 0.0021 1.0000
5.500 0.8642 0.01471 0.00913 -0.0774 0.0023 1.0000
6.750 0.9391 0.03778 0.03421 -0.0632 0.0056 1.0000
7.000 0.9471 0.04117 0.03788 -0.0601 0.0056 1.0000
7.250 0.9529 0.04465 0.04162 -0.0570 0.0056 1.0000
7.500 0.9565 0.04819 0.04540 -0.0538 0.0056 1.0000
7.750 0.9575 0.05188 0.04932 -0.0506 0.0055 1.0000
8.000 0.9569 0.05549 0.05312 -0.0475 0.0055 1.0000
8.250 0.9542 0.05906 0.05688 -0.0444 0.0055 1.0000
8.500 0.9501 0.06241 0.06037 -0.0414 0.0054 1.0000
8.750 0.9466 0.06487 0.06294 -0.0381 0.0052 1.0000
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Polar data table (+)
Polar graphs
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