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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(e422-il) EPPLER 422 AIRFOIL | Eppler E422 high lift airfoil Max thickness 14% at 24.1% chord Max camber 7.1% at 34.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e422-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e422-il | 50,000 | 9 | 5.3 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e422-il | 50,000 | 5 | 23.2 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e422-il | 100,000 | 9 | 29.5 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e422-il | 100,000 | 5 | 46.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e422-il | 200,000 | 9 | 60 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e422-il | 200,000 | 5 | 72.8 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e422-il | 500,000 | 9 | 105.8 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e422-il | 500,000 | 5 | 109 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e422-il | 1,000,000 | 9 | 140.9 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e422-il | 1,000,000 | 5 | 139.8 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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