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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(e908-il) EPPLER 908 AIRFOIL | Eppler E908 hydrofoil Max thickness 9% at 44.8% chord Max camber 2.8% at 66.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e908-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e908-il | 50,000 | 9 | 22.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e908-il | 50,000 | 5 | 24.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e908-il | 100,000 | 9 | 32.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e908-il | 100,000 | 5 | 41.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e908-il | 200,000 | 9 | 47.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e908-il | 200,000 | 5 | 62.8 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e908-il | 500,000 | 9 | 107.2 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e908-il | 500,000 | 5 | 91.8 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e908-il | 1,000,000 | 9 | 137 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e908-il | 1,000,000 | 5 | 117.9 at α=1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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