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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(e678-il) EPPLER 678 AIRFOIL | Eppler E678 sailplane airfoil Max thickness 15.1% at 39.8% chord Max camber 5.1% at 53.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e678-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e678-il | 50,000 | 9 | 22.4 at α=13.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e678-il | 50,000 | 5 | 20 at α=12.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e678-il | 100,000 | 9 | 41.5 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e678-il | 100,000 | 5 | 45.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e678-il | 200,000 | 9 | 79.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e678-il | 200,000 | 5 | 78.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e678-il | 500,000 | 9 | 116.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e678-il | 500,000 | 5 | 109.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e678-il | 1,000,000 | 9 | 141.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e678-il | 1,000,000 | 5 | 130.7 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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