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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(e583-il) EPPLER 583 AIRFOIL | Eppler E583 sailplane airfoil Max thickness 16.5% at 38% chord Max camber 4.5% at 38% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e583-il)
Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
---|---|---|---|---|---|---|---|
e583-il | 50,000 | 9 | 4.8 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
e583-il | 50,000 | 5 | 11.5 at α=11.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
e583-il | 100,000 | 9 | 32.2 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
e583-il | 100,000 | 5 | 32.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
e583-il | 200,000 | 9 | 70.4 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
e583-il | 200,000 | 5 | 70 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
e583-il | 500,000 | 9 | 111.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
e583-il | 500,000 | 5 | 107.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
e583-il | 1,000,000 | 9 | 143.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
e583-il | 1,000,000 | 5 | 132 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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