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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(e562-il) EPPLER 562 AIRFOIL | Eppler E562 general aviation airfoil Max thickness 15% at 27.6% chord Max camber 4% at 50.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e562-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e562-il | 50,000 | 9 | 11.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e562-il | 50,000 | 5 | 33.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e562-il | 100,000 | 9 | 49.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e562-il | 100,000 | 5 | 55.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e562-il | 200,000 | 9 | 73.8 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e562-il | 200,000 | 5 | 74.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e562-il | 500,000 | 9 | 104.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e562-il | 500,000 | 5 | 100.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e562-il | 1,000,000 | 9 | 129.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e562-il | 1,000,000 | 5 | 115.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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