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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(e836-il) EPPLER E836 HYDROFOIL AIRFOIL | Eppler E836 hydrofoil Max thickness 12.6% at 42.8% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e836-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e836-il | 50,000 | 9 | 28.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e836-il | 50,000 | 5 | 28.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e836-il | 100,000 | 9 | 43.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e836-il | 100,000 | 5 | 34.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e836-il | 200,000 | 9 | 45.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e836-il | 200,000 | 5 | 42.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e836-il | 500,000 | 9 | 60 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e836-il | 500,000 | 5 | 49.9 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e836-il | 1,000,000 | 9 | 67.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e836-il | 1,000,000 | 5 | 59.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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