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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(e682-il) EPPLER 682 AIRFOIL | Eppler E682 sailplane airfoil Max thickness 15.3% at 40.4% chord Max camber 2.9% at 40.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e682-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e682-il | 50,000 | 9 | 25.1 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e682-il | 50,000 | 5 | 21.5 at α=11.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e682-il | 100,000 | 9 | 43.2 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e682-il | 100,000 | 5 | 37.8 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e682-il | 200,000 | 9 | 75.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e682-il | 200,000 | 5 | 58.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e682-il | 500,000 | 9 | 91.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e682-il | 500,000 | 5 | 87.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e682-il | 1,000,000 | 9 | 115.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e682-il | 1,000,000 | 5 | 105.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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