EH 2.0/7.0 (eh2070-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: EH 2.0/7.0 (eh2070-il) Reynolds number: 500,000 Max Cl/Cd: 79.54 at α=4.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-eh2070-il-500000.txt Download as CSV file: xf-eh2070-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.500 -0.4586 0.09096 0.08902 0.0100 1.0000 0.0120
-8.250 -0.4576 0.08660 0.08467 0.0082 1.0000 0.0120
-6.000 -0.4861 0.05335 0.05094 -0.0117 1.0000 0.0126
-5.750 -0.4752 0.04868 0.04614 -0.0124 1.0000 0.0131
-5.500 -0.4599 0.04547 0.04283 -0.0127 1.0000 0.0136
-5.250 -0.4424 0.04238 0.03962 -0.0128 1.0000 0.0142
-5.000 -0.4235 0.03925 0.03632 -0.0127 1.0000 0.0149
-4.750 -0.4033 0.03605 0.03294 -0.0124 1.0000 0.0159
-4.500 -0.3817 0.03280 0.02947 -0.0118 1.0000 0.0174
-4.250 -0.3534 0.03112 0.02757 -0.0105 1.0000 0.0205
-4.000 -0.3295 0.02908 0.02523 -0.0093 1.0000 0.0209
-3.750 -0.3082 0.02625 0.02211 -0.0081 1.0000 0.0210
-3.500 -0.2867 0.01903 0.01436 -0.0076 0.9905 0.0179
-3.250 -0.2482 0.01429 0.00891 -0.0083 0.9641 0.0149
-3.000 -0.2118 0.01352 0.00797 -0.0099 0.9199 0.0175
-2.750 -0.1875 0.01189 0.00599 -0.0082 0.8723 0.0165
-2.500 -0.1646 0.01087 0.00466 -0.0065 0.8299 0.0163
-2.250 -0.1409 0.01016 0.00371 -0.0052 0.7952 0.0173
-1.750 -0.0912 0.00917 0.00234 -0.0034 0.7390 0.0254
-1.500 -0.0660 0.00869 0.00190 -0.0027 0.7153 0.0698
-1.250 -0.0403 0.00840 0.00172 -0.0023 0.6939 0.1306
-1.000 -0.0231 0.00669 0.00145 -0.0012 0.6752 0.5749
-0.750 -0.0105 0.00578 0.00155 0.0029 0.6585 0.8872
-0.500 0.0167 0.00586 0.00160 0.0038 0.6413 0.9432
-0.250 0.0524 0.00601 0.00163 0.0026 0.6238 0.9685
0.000 0.1028 0.00620 0.00163 -0.0020 0.6054 0.9804
0.250 0.1528 0.00633 0.00159 -0.0067 0.5880 0.9877
0.500 0.2003 0.00644 0.00157 -0.0109 0.5711 0.9953
0.750 0.2434 0.00647 0.00149 -0.0143 0.5550 1.0000
1.000 0.2670 0.00649 0.00143 -0.0136 0.5418 1.0000
1.250 0.2909 0.00653 0.00139 -0.0129 0.5290 1.0000
1.500 0.3148 0.00657 0.00137 -0.0122 0.5165 1.0000
1.750 0.3389 0.00663 0.00136 -0.0116 0.5039 1.0000
2.000 0.3629 0.00669 0.00138 -0.0109 0.4914 1.0000
2.250 0.3871 0.00677 0.00142 -0.0102 0.4794 1.0000
2.500 0.4114 0.00684 0.00146 -0.0096 0.4680 1.0000
2.750 0.4358 0.00693 0.00152 -0.0089 0.4570 1.0000
3.000 0.4603 0.00702 0.00160 -0.0083 0.4459 1.0000
3.250 0.4849 0.00713 0.00169 -0.0077 0.4346 1.0000
3.500 0.5096 0.00725 0.00182 -0.0071 0.4238 1.0000
3.750 0.5343 0.00738 0.00193 -0.0065 0.4118 1.0000
4.000 0.5591 0.00751 0.00206 -0.0060 0.3991 1.0000
4.250 0.5842 0.00764 0.00221 -0.0055 0.3869 1.0000
4.500 0.6091 0.00779 0.00236 -0.0050 0.3705 1.0000
4.750 0.6339 0.00797 0.00252 -0.0044 0.3410 1.0000
5.000 0.6580 0.00829 0.00268 -0.0039 0.2960 1.0000
5.250 0.6811 0.00882 0.00295 -0.0033 0.2307 1.0000
5.500 0.6952 0.01126 0.00426 -0.0021 0.0187 1.0000
5.750 0.7180 0.01220 0.00538 -0.0011 0.0123 1.0000
6.000 0.7413 0.01294 0.00626 -0.0003 0.0110 1.0000
6.250 0.7634 0.01390 0.00740 0.0006 0.0104 1.0000
6.500 0.7843 0.01508 0.00871 0.0017 0.0102 1.0000
6.750 0.8042 0.01648 0.01025 0.0030 0.0103 1.0000
7.000 0.8236 0.01822 0.01212 0.0044 0.0107 1.0000
7.250 0.8445 0.01977 0.01379 0.0055 0.0105 1.0000
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Polar data table (+)
Polar graphs
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