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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(e655-il) EPPLER 655 AIRFOIL | Eppler E655 sailplane airfoil Max thickness 17.3% at 37.3% chord Max camber 3.9% at 42.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e655-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e655-il | 50,000 | 9 | 4.9 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e655-il | 50,000 | 5 | 14.6 at α=12.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e655-il | 100,000 | 9 | 36.4 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e655-il | 100,000 | 5 | 30.7 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e655-il | 200,000 | 9 | 69.2 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e655-il | 200,000 | 5 | 69.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e655-il | 500,000 | 9 | 116.8 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e655-il | 500,000 | 5 | 111.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e655-il | 1,000,000 | 9 | 150.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e655-il | 1,000,000 | 5 | 135.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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