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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(e556-il) EPPLER 556 AIRFOIL | Eppler E556 general aviation airfoil Max thickness 16% at 31.1% chord Max camber 3.1% at 61.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e556-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e556-il | 50,000 | 9 | 25.5 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e556-il | 50,000 | 5 | 32.5 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e556-il | 100,000 | 9 | 52.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e556-il | 100,000 | 5 | 53.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e556-il | 200,000 | 9 | 72.3 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e556-il | 200,000 | 5 | 70.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e556-il | 500,000 | 9 | 97.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e556-il | 500,000 | 5 | 90.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e556-il | 1,000,000 | 9 | 116.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e556-il | 1,000,000 | 5 | 105.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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