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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(e642-il) EPPLER 642 AIRFOIL | Eppler E642 sailplane airfoil Max thickness 15.1% at 39.4% chord Max camber 3% at 39.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e642-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e642-il | 50,000 | 9 | 21.9 at α=12.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e642-il | 50,000 | 5 | 19.2 at α=12.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e642-il | 100,000 | 9 | 43.7 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e642-il | 100,000 | 5 | 43 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e642-il | 200,000 | 9 | 77.1 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e642-il | 200,000 | 5 | 65.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e642-il | 500,000 | 9 | 98.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e642-il | 500,000 | 5 | 92.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e642-il | 1,000,000 | 9 | 121.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e642-il | 1,000,000 | 5 | 109.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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