EH 2.0/7.0 (eh2070-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EH 2.0/7.0 (eh2070-il) Reynolds number: 1,000,000 Max Cl/Cd: 86.83 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eh2070-il-1000000-n5.txt Download as CSV file: xf-eh2070-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EH 2.0/7.0
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5688 0.08403 0.08260 0.0084 1.0000 0.0019
-8.000 -0.5718 0.08082 0.07941 0.0062 1.0000 0.0020
-7.750 -0.5759 0.07682 0.07542 0.0030 1.0000 0.0020
-7.500 -0.5728 0.07250 0.07107 -0.0003 1.0000 0.0021
-7.250 -0.5665 0.06836 0.06690 -0.0030 1.0000 0.0022
-7.000 -0.5576 0.06433 0.06282 -0.0054 1.0000 0.0022
-6.750 -0.5469 0.06021 0.05864 -0.0074 1.0000 0.0023
-6.500 -0.5343 0.05596 0.05431 -0.0091 1.0000 0.0025
-6.250 -0.5206 0.05133 0.04957 -0.0104 1.0000 0.0025
-6.000 -0.4945 0.04576 0.04376 -0.0140 0.9421 0.0027
-5.750 -0.4816 0.04129 0.03887 -0.0131 0.8594 0.0028
-5.500 -0.4654 0.03704 0.03426 -0.0123 0.8116 0.0030
-5.250 -0.4474 0.03213 0.02897 -0.0113 0.7792 0.0032
-5.000 -0.4281 0.02690 0.02331 -0.0099 0.7533 0.0035
-4.750 -0.4117 0.01833 0.01390 -0.0070 0.7344 0.0036
-4.500 -0.3890 0.01512 0.01011 -0.0056 0.7121 0.0039
-4.250 -0.3634 0.01403 0.00875 -0.0050 0.6903 0.0043
-4.000 -0.3366 0.01383 0.00841 -0.0048 0.6702 0.0046
-3.750 -0.3126 0.01166 0.00584 -0.0040 0.6539 0.0056
-3.500 -0.2862 0.01118 0.00523 -0.0037 0.6366 0.0061
-3.250 -0.2597 0.01075 0.00468 -0.0034 0.6208 0.0065
-3.000 -0.2331 0.01037 0.00419 -0.0031 0.6056 0.0070
-2.750 -0.2070 0.00974 0.00339 -0.0026 0.5911 0.0070
-2.500 -0.1807 0.00923 0.00273 -0.0022 0.5772 0.0069
-2.250 -0.1541 0.00887 0.00224 -0.0018 0.5636 0.0069
-2.000 -0.1271 0.00859 0.00184 -0.0015 0.5508 0.0070
-1.750 -0.1000 0.00841 0.00155 -0.0013 0.5384 0.0071
-1.500 -0.0726 0.00827 0.00132 -0.0011 0.5265 0.0074
-1.250 -0.0451 0.00816 0.00114 -0.0010 0.5147 0.0084
-1.000 -0.0177 0.00807 0.00099 -0.0009 0.5036 0.0137
-0.750 0.0095 0.00791 0.00089 -0.0007 0.4924 0.0397
-0.500 0.0368 0.00782 0.00082 -0.0007 0.4814 0.0593
-0.250 0.0640 0.00770 0.00077 -0.0006 0.4706 0.0953
0.000 0.0888 0.00704 0.00072 -0.0004 0.4603 0.3088
0.250 0.1040 0.00538 0.00064 0.0017 0.4516 0.8106
0.500 0.1296 0.00530 0.00065 0.0023 0.4424 0.8573
0.750 0.1545 0.00525 0.00068 0.0032 0.4329 0.8995
1.000 0.1804 0.00526 0.00071 0.0037 0.4231 0.9238
1.250 0.2072 0.00531 0.00075 0.0042 0.4125 0.9447
1.500 0.2362 0.00539 0.00080 0.0041 0.4009 0.9670
1.750 0.2693 0.00548 0.00084 0.0029 0.3899 0.9751
2.000 0.2989 0.00556 0.00087 0.0025 0.3795 0.9804
2.250 0.3303 0.00563 0.00091 0.0017 0.3706 0.9827
2.500 0.3623 0.00571 0.00096 0.0007 0.3620 0.9846
2.750 0.3941 0.00580 0.00102 -0.0002 0.3529 0.9865
3.000 0.4256 0.00589 0.00108 -0.0011 0.3434 0.9885
3.250 0.4565 0.00600 0.00115 -0.0019 0.3312 0.9908
3.500 0.4869 0.00611 0.00124 -0.0026 0.3196 0.9931
3.750 0.5180 0.00623 0.00136 -0.0034 0.3078 0.9948
4.000 0.5495 0.00636 0.00147 -0.0044 0.2937 0.9965
4.250 0.5800 0.00668 0.00162 -0.0053 0.2522 0.9983
4.500 0.6097 0.00719 0.00186 -0.0062 0.1918 0.9999
4.750 0.6315 0.00796 0.00226 -0.0055 0.1098 1.0000
5.000 0.6527 0.00883 0.00277 -0.0046 0.0334 1.0000
5.250 0.6759 0.00932 0.00319 -0.0039 0.0088 1.0000
5.500 0.7004 0.00959 0.00350 -0.0034 0.0069 1.0000
5.750 0.7245 0.00998 0.00393 -0.0027 0.0048 1.0000
6.000 0.7485 0.01040 0.00444 -0.0021 0.0038 1.0000
6.250 0.7730 0.01072 0.00480 -0.0016 0.0032 1.0000
6.500 0.7974 0.01111 0.00523 -0.0011 0.0027 1.0000
6.750 0.8217 0.01154 0.00571 -0.0006 0.0023 1.0000
7.000 0.8457 0.01204 0.00628 -0.0001 0.0021 1.0000
7.250 0.8692 0.01263 0.00698 0.0004 0.0020 1.0000
7.500 0.8917 0.01343 0.00790 0.0011 0.0018 1.0000
7.750 0.9106 0.01486 0.00952 0.0022 0.0015 1.0000
8.000 0.9342 0.01537 0.01008 0.0026 0.0014 1.0000
8.250 0.9575 0.01591 0.01069 0.0030 0.0013 1.0000
8.500 0.9786 0.01684 0.01173 0.0038 0.0012 1.0000
8.750 0.9983 0.01797 0.01300 0.0046 0.0011 1.0000
9.000 1.0156 0.01951 0.01472 0.0058 0.0010 1.0000
9.250 1.0310 0.02136 0.01679 0.0071 0.0009 1.0000
9.500 1.0438 0.02369 0.01937 0.0087 0.0009 1.0000
9.750 1.0532 0.02648 0.02246 0.0104 0.0009 1.0000
10.000 1.0558 0.03020 0.02655 0.0125 0.0009 1.0000
10.250 1.0520 0.03424 0.03094 0.0148 0.0009 1.0000
10.500 1.0390 0.03822 0.03523 0.0177 0.0009 1.0000
10.750 1.0226 0.04134 0.03854 0.0200 0.0009 1.0000
11.000 1.0011 0.04601 0.04343 0.0197 0.0009 1.0000
11.250 0.9913 0.04986 0.04741 0.0179 0.0009 1.0000
11.500 0.9691 0.05647 0.05420 0.0141 0.0009 1.0000
11.750 0.9524 0.06285 0.06073 0.0098 0.0009 1.0000
12.000 0.9348 0.07000 0.06801 0.0048 0.0009 1.0000
12.250 0.9224 0.07663 0.07473 0.0002 0.0009 1.0000
12.500 0.9078 0.08418 0.08238 -0.0049 0.0009 1.0000
12.750 0.8883 0.09363 0.09192 -0.0110 0.0009 1.0000
13.000 0.8726 0.10287 0.10123 -0.0165 0.0009 1.0000
13.250 0.8557 0.11352 0.11195 -0.0220 0.0010 1.0000
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Polar data table (+)
Polar graphs
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