Eh 1.0/7.0 (eh1070-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: Eh 1.0/7.0 (eh1070-il) Reynolds number: 1,000,000 Max Cl/Cd: 66.61 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eh1070-il-1000000-n5.txt Download as CSV file: xf-eh1070-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: Eh 1.0/7.0
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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.6240 0.08423 0.08272 0.0068 1.0000 0.0017
-8.500 -0.6311 0.07913 0.07765 0.0035 1.0000 0.0017
-8.250 -0.6421 0.07460 0.07315 -0.0005 1.0000 0.0017
-8.000 -0.6495 0.06853 0.06704 -0.0049 1.0000 0.0017
-7.750 -0.6515 0.06241 0.06085 -0.0083 1.0000 0.0016
-7.500 -0.6529 0.05523 0.05353 -0.0109 1.0000 0.0016
-7.000 -0.6902 0.01975 0.01604 -0.0072 1.0000 0.0020
-6.750 -0.6683 0.01801 0.01404 -0.0064 1.0000 0.0021
-6.500 -0.6444 0.01698 0.01283 -0.0059 1.0000 0.0022
-6.250 -0.6201 0.01610 0.01181 -0.0054 1.0000 0.0023
-6.000 -0.5990 0.01381 0.00916 -0.0043 1.0000 0.0026
-5.750 -0.5746 0.01295 0.00817 -0.0038 1.0000 0.0028
-5.500 -0.5495 0.01238 0.00752 -0.0034 1.0000 0.0030
-5.250 -0.5245 0.01175 0.00682 -0.0029 1.0000 0.0032
-5.000 -0.4994 0.01123 0.00623 -0.0024 1.0000 0.0034
-4.750 -0.4690 0.01071 0.00561 -0.0031 0.9908 0.0039
-4.500 -0.4352 0.01020 0.00504 -0.0045 0.9759 0.0046
-4.250 -0.4019 0.00971 0.00446 -0.0057 0.9532 0.0052
-4.000 -0.3740 0.00954 0.00419 -0.0056 0.9184 0.0055
-3.750 -0.3515 0.00880 0.00320 -0.0043 0.8811 0.0067
-3.500 -0.3270 0.00854 0.00276 -0.0034 0.8462 0.0074
-3.250 -0.3015 0.00835 0.00243 -0.0028 0.8139 0.0081
-3.000 -0.2754 0.00818 0.00211 -0.0024 0.7855 0.0086
-2.750 -0.2489 0.00804 0.00179 -0.0020 0.7588 0.0089
-2.500 -0.2221 0.00794 0.00156 -0.0017 0.7338 0.0095
-2.250 -0.1952 0.00786 0.00137 -0.0014 0.7094 0.0112
-2.000 -0.1685 0.00770 0.00120 -0.0012 0.6854 0.0296
-1.750 -0.1418 0.00755 0.00107 -0.0010 0.6626 0.0583
-1.500 -0.1148 0.00744 0.00094 -0.0009 0.6415 0.0817
-1.250 -0.0881 0.00727 0.00084 -0.0008 0.6213 0.1241
-1.000 -0.0621 0.00693 0.00075 -0.0006 0.6021 0.2180
-0.750 -0.0382 0.00617 0.00063 -0.0003 0.5838 0.4285
-0.250 0.0115 0.00538 0.00053 0.0005 0.5484 0.6789
0.000 0.0375 0.00524 0.00051 0.0009 0.5314 0.7390
0.250 0.0632 0.00513 0.00053 0.0014 0.5150 0.7932
0.500 0.0890 0.00509 0.00055 0.0020 0.4971 0.8372
0.750 0.1142 0.00505 0.00059 0.0027 0.4776 0.8752
1.000 0.1384 0.00505 0.00065 0.0037 0.4596 0.9185
1.250 0.1647 0.00510 0.00070 0.0043 0.4448 0.9440
1.500 0.1931 0.00517 0.00074 0.0042 0.4316 0.9559
1.750 0.2229 0.00525 0.00078 0.0038 0.4166 0.9643
2.000 0.2532 0.00536 0.00083 0.0033 0.3980 0.9707
2.250 0.2844 0.00549 0.00091 0.0025 0.3767 0.9758
2.500 0.3139 0.00562 0.00097 0.0020 0.3568 0.9815
2.750 0.3469 0.00576 0.00105 0.0008 0.3353 0.9844
3.000 0.3790 0.00593 0.00115 -0.0003 0.3111 0.9874
3.250 0.4103 0.00616 0.00126 -0.0012 0.2763 0.9906
3.500 0.4396 0.00663 0.00147 -0.0019 0.2067 0.9937
3.750 0.4706 0.00711 0.00169 -0.0030 0.1423 0.9959
4.000 0.5006 0.00783 0.00204 -0.0040 0.0579 0.9985
4.250 0.5293 0.00833 0.00236 -0.0045 0.0188 1.0000
4.500 0.5534 0.00861 0.00262 -0.0038 0.0109 1.0000
4.750 0.5778 0.00888 0.00291 -0.0031 0.0071 1.0000
5.000 0.6024 0.00913 0.00319 -0.0026 0.0057 1.0000
5.250 0.6269 0.00944 0.00357 -0.0020 0.0048 1.0000
5.500 0.6511 0.00986 0.00404 -0.0013 0.0039 1.0000
5.750 0.6750 0.01040 0.00468 -0.0006 0.0032 1.0000
6.000 0.6995 0.01081 0.00515 0.0000 0.0029 1.0000
6.250 0.7232 0.01145 0.00590 0.0007 0.0026 1.0000
6.500 0.7462 0.01227 0.00685 0.0015 0.0025 1.0000
6.750 0.7683 0.01328 0.00800 0.0024 0.0024 1.0000
7.000 0.7899 0.01446 0.00934 0.0034 0.0023 1.0000
7.250 0.8106 0.01591 0.01096 0.0045 0.0023 1.0000
7.500 0.8309 0.01757 0.01285 0.0056 0.0023 1.0000
7.750 0.8505 0.01952 0.01504 0.0068 0.0023 1.0000
8.000 0.8702 0.02128 0.01701 0.0077 0.0022 1.0000
8.250 0.8899 0.02281 0.01873 0.0086 0.0020 1.0000
8.500 0.9080 0.02459 0.02073 0.0095 0.0019 1.0000
8.750 0.9256 0.02623 0.02257 0.0104 0.0018 1.0000
9.000 0.9372 0.02911 0.02576 0.0117 0.0018 1.0000
9.250 0.9451 0.03231 0.02927 0.0132 0.0017 1.0000
9.500 0.9490 0.03568 0.03293 0.0146 0.0017 1.0000
9.750 0.9412 0.04033 0.03791 0.0165 0.0017 1.0000
10.000 0.9342 0.04367 0.04145 0.0180 0.0016 1.0000
10.250 0.9109 0.04743 0.04539 0.0201 0.0016 1.0000
10.500 0.8998 0.05063 0.04869 0.0189 0.0016 1.0000
10.750 0.8716 0.05828 0.05652 0.0133 0.0017 1.0000
11.000 0.8459 0.06814 0.06653 0.0050 0.0017 1.0000
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Polar data table (+)
Polar graphs
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