E61 (5.64%) (e61-il)
E61 (5.64%) - Eppler E61 low Reynolds number airfoil
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(e61-il) E61 (5.64%) Eppler E61 low Reynolds number airfoil Max thickness 5.7% at 23.8% chord. Max camber 6.4% at 51% chord Source UIUC Airfoil Coordinates Database Source dat file The dat file is in Selig format |
E61 (5.64%) 1.00000 0.00000 0.99707 0.00124 0.98882 0.00495 0.97619 0.01076 0.95978 0.01777 0.93951 0.02510 0.91507 0.03246 0.88654 0.03992 0.85426 0.04744 0.81861 0.05486 0.77996 0.06205 0.73876 0.06884 0.69546 0.07510 0.65052 0.08061 0.60439 0.08517 0.55742 0.08861 0.50997 0.09083 0.46240 0.09182 0.41512 0.09163 0.36860 0.09031 0.32329 0.08789 0.27963 0.08441 0.23803 0.07993 0.19889 0.07452 0.16256 0.06827 0.12936 0.06127 0.09957 0.05366 0.07343 0.04557 0.05112 0.03719 0.03278 0.02870 0.01850 0.02034 0.00831 0.01243 0.00221 0.00532 0.00001 -0.00029 0.00285 -0.00329 0.01170 -0.00421 0.02628 -0.00370 0.04664 -0.00168 0.07273 0.00159 0.10442 0.00593 0.14147 0.01102 0.18354 0.01659 0.23017 0.02233 0.28082 0.02793 0.33487 0.03310 0.39164 0.03752 0.45026 0.04086 0.50974 0.04298 0.56915 0.04389 0.62767 0.04362 0.68446 0.04219 0.73873 0.03969 0.78969 0.03619 0.83661 0.03184 0.87879 0.02677 0.91559 0.02122 0.94642 0.01533 0.97050 0.00942 0.98725 0.00435 0.99688 0.00109 1.00000 0.00000 |
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Polars for E61 (5.64%) (e61-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e61-il | 50,000 | 9 | 46.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e61-il | 50,000 | 5 | 45.4 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e61-il | 100,000 | 9 | 75.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e61-il | 100,000 | 5 | 75.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e61-il | 200,000 | 9 | 112.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e61-il | 200,000 | 5 | 110.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e61-il | 500,000 | 9 | 171 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e61-il | 500,000 | 5 | 157.1 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e61-il | 1,000,000 | 9 | 214.8 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e61-il | 1,000,000 | 5 | 176.6 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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