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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(e604-il) EPPLER 604 AIRFOIL | Eppler E604 sailplane airfoil Max thickness 18.8% at 37.3% chord Max camber 3.4% at 42.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e604-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e604-il | 50,000 | 9 | 5.2 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e604-il | 50,000 | 5 | 13.8 at α=14.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e604-il | 100,000 | 9 | 34.1 at α=12.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e604-il | 100,000 | 5 | 30.1 at α=10.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e604-il | 200,000 | 9 | 65.1 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e604-il | 200,000 | 5 | 67.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e604-il | 500,000 | 9 | 106.7 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e604-il | 500,000 | 5 | 101.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e604-il | 1,000,000 | 9 | 136.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e604-il | 1,000,000 | 5 | 123.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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