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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(e657-il) EPPLER 657 AIRFOIL | Eppler E657 sailplane airfoil Max thickness 15.6% at 37% chord Max camber 4.6% at 47.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e657-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e657-il | 50,000 | 9 | 7.5 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e657-il | 50,000 | 5 | 18.7 at α=12° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e657-il | 100,000 | 9 | 41.7 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e657-il | 100,000 | 5 | 35.3 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e657-il | 200,000 | 9 | 72 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e657-il | 200,000 | 5 | 70.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e657-il | 500,000 | 9 | 126.2 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e657-il | 500,000 | 5 | 117.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e657-il | 1,000,000 | 9 | 160.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e657-il | 1,000,000 | 5 | 145 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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