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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(e420-il) EPPLER 420 AIRFOIL | Eppler E420 high lift airfoil Max thickness 14.3% at 22.8% chord Max camber 10.6% at 40.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e420-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e420-il | 50,000 | 9 | 5.3 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e420-il | 50,000 | 5 | 13.3 at α=0.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e420-il | 100,000 | 9 | 20 at α=0.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e420-il | 100,000 | 5 | 47.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e420-il | 200,000 | 9 | 63.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e420-il | 200,000 | 5 | 75.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e420-il | 500,000 | 9 | 107.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e420-il | 500,000 | 5 | 106.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e420-il | 1,000,000 | 9 | 137.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e420-il | 1,000,000 | 5 | 134.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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