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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(e340-il) EPPLER 340 AIRFOIL | Eppler E340 flying wing airfoil Max thickness 13.7% at 28.8% chord Max camber 2.6% at 19.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e340-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e340-il | 50,000 | 9 | 13.6 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e340-il | 50,000 | 5 | 22.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e340-il | 100,000 | 9 | 28.4 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e340-il | 100,000 | 5 | 42.1 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e340-il | 200,000 | 9 | 58.7 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e340-il | 200,000 | 5 | 57 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e340-il | 500,000 | 9 | 80.3 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e340-il | 500,000 | 5 | 74.3 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e340-il | 1,000,000 | 9 | 94.2 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e340-il | 1,000,000 | 5 | 93.7 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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