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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(e904-il) EPPLER 904 AIRFOIL | Eppler E904 hydrofoil Max thickness 9% at 44.9% chord Max camber 1.3% at 50.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e904-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e904-il | 50,000 | 9 | 21.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e904-il | 50,000 | 5 | 24 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e904-il | 100,000 | 9 | 29.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e904-il | 100,000 | 5 | 41.9 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e904-il | 200,000 | 9 | 61.5 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e904-il | 200,000 | 5 | 53.9 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e904-il | 500,000 | 9 | 67.1 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e904-il | 500,000 | 5 | 72.4 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e904-il | 1,000,000 | 9 | 86.9 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e904-il | 1,000,000 | 5 | 87.7 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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