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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(e334-il) EPPLER 334 AIRFOIL | Eppler E334 flying wing airfoil Max thickness 11.9% at 30.3% chord Max camber 4% at 25.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e334-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e334-il | 50,000 | 9 | 16.6 at α=0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e334-il | 50,000 | 5 | 27.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e334-il | 100,000 | 9 | 39.9 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e334-il | 100,000 | 5 | 48.6 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e334-il | 200,000 | 9 | 66.1 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e334-il | 200,000 | 5 | 70 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e334-il | 500,000 | 9 | 100.8 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e334-il | 500,000 | 5 | 98.4 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e334-il | 1,000,000 | 9 | 125.6 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e334-il | 1,000,000 | 5 | 116.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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