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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(e580-il) EPPLER 580 AIRFOIL | Eppler E580 general purpose airfoil Max thickness 16.1% at 33% chord Max camber 4.1% at 61.2% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e580-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e580-il | 50,000 | 9 | 7.5 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e580-il | 50,000 | 5 | 24.4 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e580-il | 100,000 | 9 | 52.1 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e580-il | 100,000 | 5 | 54.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e580-il | 200,000 | 9 | 76.1 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e580-il | 200,000 | 5 | 76.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e580-il | 500,000 | 9 | 107.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e580-il | 500,000 | 5 | 102 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e580-il | 1,000,000 | 9 | 131.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e580-il | 1,000,000 | 5 | 120.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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