Eh 1.0/7.0 (eh1070-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
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Airfoil: Eh 1.0/7.0 (eh1070-il) Reynolds number: 1,000,000 Max Cl/Cd: 76.98 at α=3.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eh1070-il-1000000.txt Download as CSV file: xf-eh1070-il-1000000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.6080 0.08152 0.08003 0.0043 1.0000 0.0063
-8.000 -0.6176 0.07690 0.07544 0.0005 1.0000 0.0061
-7.750 -0.6219 0.07145 0.06997 -0.0039 1.0000 0.0066
-7.500 -0.6215 0.06611 0.06457 -0.0073 1.0000 0.0064
-7.250 -0.6143 0.06078 0.05916 -0.0098 1.0000 0.0070
-7.000 -0.5978 0.05686 0.05515 -0.0110 1.0000 0.0075
-6.750 -0.5884 0.05138 0.04952 -0.0120 1.0000 0.0076
-6.500 -0.5778 0.04581 0.04377 -0.0123 1.0000 0.0076
-6.250 -0.5658 0.04043 0.03815 -0.0120 1.0000 0.0077
-6.000 -0.5523 0.03571 0.03315 -0.0112 1.0000 0.0077
-5.750 -0.5531 0.02575 0.02249 -0.0094 1.0000 0.0085
-5.500 -0.5331 0.02364 0.02017 -0.0087 1.0000 0.0090
-5.250 -0.5109 0.02250 0.01892 -0.0083 1.0000 0.0098
-5.000 -0.4875 0.02154 0.01783 -0.0077 1.0000 0.0114
-4.750 -0.4630 0.02026 0.01638 -0.0068 1.0000 0.0128
-4.500 -0.4425 0.01467 0.01004 -0.0039 1.0000 0.0081
-4.250 -0.4196 0.01262 0.00780 -0.0025 1.0000 0.0072
-4.000 -0.3968 0.01112 0.00611 -0.0012 1.0000 0.0072
-3.750 -0.3737 0.01022 0.00511 -0.0001 1.0000 0.0075
-3.500 -0.3498 0.00873 0.00344 0.0008 0.9986 0.0091
-3.250 -0.3140 0.00820 0.00284 -0.0009 0.9918 0.0104
-3.000 -0.2776 0.00784 0.00245 -0.0028 0.9832 0.0120
-2.750 -0.2423 0.00751 0.00206 -0.0044 0.9694 0.0138
-2.500 -0.2114 0.00693 0.00155 -0.0049 0.9457 0.0544
-2.250 -0.1859 0.00665 0.00137 -0.0043 0.9136 0.1035
-2.000 -0.1623 0.00632 0.00121 -0.0034 0.8799 0.1808
-1.750 -0.1392 0.00583 0.00105 -0.0026 0.8484 0.3085
-1.500 -0.1181 0.00496 0.00088 -0.0016 0.8184 0.5478
-1.250 -0.0959 0.00446 0.00079 -0.0005 0.7895 0.7023
-1.000 -0.0720 0.00427 0.00076 0.0005 0.7621 0.7831
-0.750 -0.0473 0.00421 0.00075 0.0014 0.7362 0.8360
-0.250 0.0033 0.00421 0.00073 0.0029 0.6869 0.8959
0.000 0.0291 0.00426 0.00072 0.0036 0.6642 0.9163
0.500 0.0816 0.00440 0.00076 0.0047 0.6204 0.9540
0.750 0.1108 0.00451 0.00079 0.0046 0.5973 0.9693
1.000 0.1465 0.00466 0.00085 0.0030 0.5744 0.9820
1.250 0.1878 0.00477 0.00088 0.0001 0.5535 0.9854
1.500 0.2240 0.00487 0.00091 -0.0018 0.5327 0.9883
1.750 0.2586 0.00497 0.00093 -0.0034 0.5119 0.9914
2.000 0.2920 0.00509 0.00099 -0.0047 0.4889 0.9943
2.750 0.3935 0.00541 0.00111 -0.0090 0.4208 1.0000
3.000 0.4173 0.00555 0.00119 -0.0083 0.3965 1.0000
3.250 0.4411 0.00573 0.00127 -0.0076 0.3630 1.0000
3.500 0.4644 0.00604 0.00138 -0.0068 0.3093 1.0000
3.750 0.4878 0.00636 0.00152 -0.0061 0.2615 1.0000
4.000 0.5105 0.00685 0.00173 -0.0054 0.1925 1.0000
4.250 0.5321 0.00758 0.00207 -0.0046 0.1027 1.0000
4.500 0.5530 0.00859 0.00269 -0.0035 0.0146 1.0000
4.750 0.5770 0.00908 0.00327 -0.0027 0.0100 1.0000
5.000 0.6014 0.00942 0.00366 -0.0020 0.0086 1.0000
5.250 0.6256 0.00986 0.00417 -0.0013 0.0077 1.0000
5.500 0.6492 0.01043 0.00480 -0.0005 0.0065 1.0000
5.750 0.6682 0.01210 0.00670 0.0011 0.0054 1.0000
6.000 0.6911 0.01296 0.00767 0.0020 0.0052 1.0000
6.250 0.7125 0.01432 0.00917 0.0032 0.0051 1.0000
6.500 0.7327 0.01639 0.01141 0.0045 0.0053 1.0000
7.000 0.7627 0.02801 0.02403 0.0091 0.0104 1.0000
7.250 0.7821 0.02969 0.02595 0.0101 0.0102 1.0000
7.500 0.8110 0.02836 0.02466 0.0106 0.0088 1.0000
7.750 0.8302 0.03000 0.02649 0.0114 0.0079 1.0000
8.000 0.8465 0.03204 0.02872 0.0123 0.0073 1.0000
8.250 0.8621 0.03367 0.03049 0.0129 0.0067 1.0000
8.500 0.8746 0.03589 0.03286 0.0136 0.0065 1.0000
8.750 0.8825 0.03867 0.03585 0.0146 0.0062 1.0000
9.000 0.8841 0.04212 0.03955 0.0156 0.0061 1.0000
9.250 0.8768 0.04631 0.04396 0.0166 0.0059 1.0000
9.500 0.8557 0.05097 0.04884 0.0181 0.0058 1.0000
9.750 0.8365 0.05429 0.05228 0.0187 0.0057 1.0000
10.000 0.8244 0.05801 0.05611 0.0165 0.0058 1.0000
10.250 0.8092 0.06371 0.06190 0.0115 0.0058 1.0000
10.500 0.8046 0.06927 0.06757 0.0064 0.0060 1.0000
10.750 0.7853 0.08013 0.07856 -0.0023 0.0062 1.0000
11.000 0.7569 0.09806 0.09652 -0.0116 0.0065 1.0000
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Polar data table (+)
Polar graphs
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