Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
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(e817-il) EPPLER 817 HYDROFOIL AIRFOIL | Eppler E817 hydrofoil Max thickness 11% at 32.9% chord Max camber 2.9% at 66.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e817-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e817-il | 50,000 | 9 | 26.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e817-il | 50,000 | 5 | 29.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e817-il | 100,000 | 9 | 40.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e817-il | 100,000 | 5 | 47.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e817-il | 200,000 | 9 | 79.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e817-il | 200,000 | 5 | 71.3 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e817-il | 500,000 | 9 | 113.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e817-il | 500,000 | 5 | 98.2 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e817-il | 1,000,000 | 9 | 138.1 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e817-il | 1,000,000 | 5 | 112.4 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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