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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(e598-il) EPPLER 598 AIRFOIL | Eppler E598 airfoil Max thickness 11.1% at 24.2% chord Max camber 4.5% at 34.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e598-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e598-il | 50,000 | 9 | 9.9 at α=0° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e598-il | 50,000 | 5 | 23.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e598-il | 100,000 | 9 | 43.3 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e598-il | 100,000 | 5 | 50.6 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e598-il | 200,000 | 9 | 72.2 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e598-il | 200,000 | 5 | 75.6 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e598-il | 500,000 | 9 | 109.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e598-il | 500,000 | 5 | 106.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e598-il | 1,000,000 | 9 | 137.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e598-il | 1,000,000 | 5 | 128.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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