EH 2.0/10 (eh2010-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EH 2.0/10 (eh2010-il) Reynolds number: 1,000,000 Max Cl/Cd: 94.92 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-eh2010-il-1000000-n5.txt Download as CSV file: xf-eh2010-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EH 2.0/10
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
------ -------- --------- --------- -------- -------- --------
-12.250 -1.0393 0.03795 0.03565 -0.0266 1.0000 0.0033
-12.000 -1.0461 0.03437 0.03180 -0.0244 1.0000 0.0034
-11.750 -1.0445 0.03156 0.02874 -0.0224 1.0000 0.0034
-11.500 -1.0378 0.02922 0.02618 -0.0207 1.0000 0.0035
-11.250 -1.0280 0.02712 0.02383 -0.0191 1.0000 0.0035
-11.000 -1.0120 0.02578 0.02233 -0.0179 1.0000 0.0036
-10.750 -0.9968 0.02425 0.02061 -0.0166 1.0000 0.0036
-10.500 -0.9789 0.02303 0.01924 -0.0155 1.0000 0.0036
-10.250 -0.9601 0.02188 0.01793 -0.0145 1.0000 0.0037
-10.000 -0.9463 0.01984 0.01562 -0.0128 1.0000 0.0039
-9.750 -0.9267 0.01869 0.01430 -0.0118 1.0000 0.0041
-9.500 -0.9051 0.01783 0.01335 -0.0110 1.0000 0.0043
-9.250 -0.8822 0.01719 0.01264 -0.0103 1.0000 0.0045
-9.000 -0.8585 0.01670 0.01209 -0.0097 1.0000 0.0047
-8.750 -0.8353 0.01608 0.01138 -0.0090 1.0000 0.0049
-8.500 -0.8117 0.01553 0.01076 -0.0084 1.0000 0.0052
-8.250 -0.7883 0.01494 0.01009 -0.0077 1.0000 0.0053
-8.000 -0.7553 0.01427 0.00932 -0.0091 0.9768 0.0056
-7.750 -0.7200 0.01365 0.00856 -0.0108 0.9340 0.0057
-7.500 -0.6976 0.01331 0.00802 -0.0096 0.8843 0.0059
-7.250 -0.6749 0.01295 0.00745 -0.0085 0.8456 0.0060
-7.000 -0.6511 0.01262 0.00693 -0.0077 0.8136 0.0061
-6.750 -0.6275 0.01208 0.00621 -0.0068 0.7855 0.0064
-6.500 -0.6028 0.01168 0.00567 -0.0062 0.7602 0.0069
-6.250 -0.5774 0.01138 0.00527 -0.0057 0.7381 0.0075
-6.000 -0.5516 0.01114 0.00494 -0.0053 0.7175 0.0082
-5.750 -0.5256 0.01090 0.00460 -0.0049 0.6990 0.0088
-5.500 -0.4993 0.01067 0.00427 -0.0045 0.6812 0.0093
-5.250 -0.4734 0.01037 0.00389 -0.0041 0.6646 0.0107
-5.000 -0.4470 0.01016 0.00362 -0.0038 0.6488 0.0123
-4.750 -0.4204 0.00999 0.00338 -0.0036 0.6340 0.0136
-4.500 -0.3935 0.00984 0.00315 -0.0033 0.6202 0.0146
-4.250 -0.3670 0.00963 0.00289 -0.0030 0.6067 0.0170
-4.000 -0.3401 0.00946 0.00268 -0.0028 0.5940 0.0191
-3.750 -0.3131 0.00933 0.00248 -0.0026 0.5815 0.0209
-3.500 -0.2862 0.00917 0.00229 -0.0024 0.5700 0.0251
-3.250 -0.2593 0.00902 0.00212 -0.0022 0.5583 0.0316
-3.000 -0.2323 0.00888 0.00197 -0.0020 0.5469 0.0403
-2.750 -0.2052 0.00874 0.00183 -0.0018 0.5363 0.0497
-2.500 -0.1779 0.00864 0.00171 -0.0016 0.5262 0.0582
-2.250 -0.1506 0.00854 0.00159 -0.0015 0.5162 0.0668
-2.000 -0.1233 0.00844 0.00149 -0.0014 0.5058 0.0788
-1.750 -0.0960 0.00834 0.00140 -0.0012 0.4963 0.0925
-1.500 -0.0689 0.00822 0.00131 -0.0011 0.4867 0.1150
-1.250 -0.0420 0.00806 0.00124 -0.0009 0.4772 0.1510
-1.000 -0.0151 0.00790 0.00117 -0.0008 0.4685 0.1889
-0.750 0.0117 0.00774 0.00110 -0.0006 0.4596 0.2317
-0.500 0.0381 0.00752 0.00104 -0.0004 0.4508 0.2950
-0.250 0.0624 0.00703 0.00095 0.0000 0.4428 0.4319
0.000 0.0837 0.00631 0.00087 0.0011 0.4344 0.6351
0.250 0.1073 0.00597 0.00087 0.0020 0.4268 0.7442
0.500 0.1326 0.00587 0.00090 0.0027 0.4184 0.7994
0.750 0.1591 0.00583 0.00093 0.0031 0.4102 0.8304
1.000 0.1858 0.00584 0.00097 0.0035 0.4027 0.8548
1.250 0.2123 0.00585 0.00102 0.0039 0.3941 0.8764
1.500 0.2386 0.00588 0.00107 0.0044 0.3868 0.8987
1.750 0.2651 0.00594 0.00113 0.0049 0.3784 0.9137
2.000 0.2927 0.00599 0.00117 0.0050 0.3707 0.9204
2.500 0.3482 0.00614 0.00127 0.0051 0.3549 0.9319
2.750 0.3759 0.00622 0.00133 0.0052 0.3475 0.9379
3.000 0.4038 0.00631 0.00139 0.0052 0.3393 0.9432
3.250 0.4321 0.00640 0.00147 0.0051 0.3319 0.9486
3.500 0.4596 0.00650 0.00154 0.0052 0.3235 0.9543
3.750 0.4891 0.00660 0.00164 0.0048 0.3157 0.9584
4.000 0.5183 0.00672 0.00173 0.0045 0.3076 0.9630
4.250 0.5464 0.00682 0.00182 0.0044 0.2992 0.9681
4.500 0.5772 0.00695 0.00193 0.0037 0.2910 0.9711
4.750 0.6081 0.00709 0.00206 0.0029 0.2815 0.9741
5.000 0.6382 0.00722 0.00218 0.0024 0.2725 0.9775
5.250 0.6668 0.00737 0.00232 0.0021 0.2637 0.9815
5.500 0.6983 0.00755 0.00247 0.0011 0.2530 0.9835
5.750 0.7299 0.00778 0.00265 0.0001 0.2336 0.9852
6.000 0.7610 0.00806 0.00285 -0.0009 0.2138 0.9871
6.250 0.7916 0.00834 0.00306 -0.0018 0.1961 0.9893
6.500 0.8205 0.00879 0.00337 -0.0024 0.1631 0.9919
6.750 0.8487 0.00936 0.00375 -0.0031 0.1265 0.9943
7.000 0.8773 0.01015 0.00430 -0.0040 0.0806 0.9964
7.250 0.9054 0.01096 0.00489 -0.0048 0.0423 0.9987
7.500 0.9317 0.01156 0.00539 -0.0051 0.0232 1.0000
7.750 0.9521 0.01197 0.00578 -0.0039 0.0167 1.0000
8.000 0.9731 0.01235 0.00616 -0.0029 0.0127 1.0000
8.250 0.9940 0.01276 0.00659 -0.0018 0.0091 1.0000
8.500 1.0148 0.01320 0.00703 -0.0008 0.0065 1.0000
8.750 1.0355 0.01366 0.00750 0.0003 0.0048 1.0000
9.000 1.0567 0.01409 0.00796 0.0012 0.0041 1.0000
9.250 1.0779 0.01452 0.00844 0.0021 0.0036 1.0000
9.500 1.0988 0.01501 0.00896 0.0030 0.0031 1.0000
9.750 1.1192 0.01553 0.00953 0.0039 0.0028 1.0000
10.000 1.1383 0.01618 0.01024 0.0050 0.0025 1.0000
10.250 1.1576 0.01678 0.01092 0.0060 0.0024 1.0000
10.500 1.1769 0.01735 0.01155 0.0070 0.0023 1.0000
10.750 1.1951 0.01799 0.01226 0.0081 0.0023 1.0000
11.000 1.2120 0.01869 0.01303 0.0093 0.0022 1.0000
11.250 1.2285 0.01937 0.01377 0.0105 0.0020 1.0000
11.500 1.2417 0.02021 0.01470 0.0121 0.0020 1.0000
11.750 1.2544 0.02100 0.01556 0.0138 0.0019 1.0000
12.000 1.2607 0.02186 0.01650 0.0164 0.0019 1.0000
12.250 1.2649 0.02285 0.01756 0.0190 0.0018 1.0000
12.500 1.2685 0.02402 0.01884 0.0211 0.0018 1.0000
12.750 1.2702 0.02556 0.02047 0.0227 0.0017 1.0000
13.000 1.2737 0.02720 0.02220 0.0235 0.0016 1.0000
13.250 1.2764 0.02916 0.02424 0.0239 0.0016 1.0000
13.500 1.2750 0.03175 0.02695 0.0239 0.0016 1.0000
13.750 1.2726 0.03469 0.03001 0.0234 0.0017 1.0000
14.000 1.2724 0.03755 0.03296 0.0227 0.0016 1.0000
14.250 1.2653 0.04135 0.03689 0.0216 0.0016 1.0000
14.500 1.2635 0.04458 0.04019 0.0206 0.0015 1.0000
14.750 1.2571 0.04847 0.04419 0.0193 0.0015 1.0000
15.000 1.2488 0.05268 0.04852 0.0178 0.0015 1.0000
15.250 1.2363 0.05756 0.05349 0.0159 0.0013 1.0000
15.500 1.2296 0.06171 0.05776 0.0143 0.0014 1.0000
15.750 1.2183 0.06671 0.06285 0.0122 0.0014 1.0000
16.000 1.1916 0.07425 0.07054 0.0089 0.0013 1.0000
16.250 1.1879 0.07849 0.07487 0.0070 0.0013 1.0000
16.500 1.1807 0.08335 0.07982 0.0048 0.0013 1.0000
16.750 1.1602 0.09063 0.08723 0.0013 0.0013 1.0000
17.000 1.1557 0.09531 0.09198 -0.0009 0.0013 1.0000
17.250 1.1456 0.10105 0.09783 -0.0037 0.0013 1.0000
17.500 1.1355 0.10697 0.10385 -0.0066 0.0013 1.0000
17.750 1.1223 0.11359 0.11057 -0.0100 0.0013 1.0000
18.000 1.1095 0.12030 0.11738 -0.0135 0.0013 1.0000
18.250 1.1039 0.12572 0.12288 -0.0163 0.0014 1.0000
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Polar data table (+)
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