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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(e559-il) EPPLER 559 AIRFOIL | Eppler E559 general aviation airfoil Max thickness 16% at 27.2% chord Max camber 4.3% at 50.2% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e559-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e559-il | 50,000 | 9 | 8.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e559-il | 50,000 | 5 | 30.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e559-il | 100,000 | 9 | 43.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e559-il | 100,000 | 5 | 52.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e559-il | 200,000 | 9 | 70.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e559-il | 200,000 | 5 | 73.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e559-il | 500,000 | 9 | 103.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e559-il | 500,000 | 5 | 101.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e559-il | 1,000,000 | 9 | 130.6 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e559-il | 1,000,000 | 5 | 123.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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