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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(e342-il) EPPLER 342 AIRFOIL | Eppler E342 flying wing airfoil Max thickness 14.3% at 31.8% chord Max camber 3.5% at 22.2% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e342-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e342-il | 50,000 | 9 | 14.6 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e342-il | 50,000 | 5 | 24.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e342-il | 100,000 | 9 | 30.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e342-il | 100,000 | 5 | 43.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e342-il | 200,000 | 9 | 59.4 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e342-il | 200,000 | 5 | 61.9 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e342-il | 500,000 | 9 | 88.3 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e342-il | 500,000 | 5 | 83.7 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e342-il | 1,000,000 | 9 | 108.3 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e342-il | 1,000,000 | 5 | 106.3 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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