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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(e421-il) EPPLER 421 AIRFOIL | Eppler E421 high lift airfoil Max thickness 14.5% at 26% chord Max camber 8.6% at 37.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e421-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e421-il | 50,000 | 9 | 5.3 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e421-il | 50,000 | 5 | 20 at α=0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e421-il | 100,000 | 9 | 27.7 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e421-il | 100,000 | 5 | 48 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e421-il | 200,000 | 9 | 63 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e421-il | 200,000 | 5 | 74.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e421-il | 500,000 | 9 | 107.4 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e421-il | 500,000 | 5 | 109.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e421-il | 1,000,000 | 9 | 141.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e421-il | 1,000,000 | 5 | 141.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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