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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(e593-il) EPPLER 593 AIRFOIL | Eppler E593 airfoil Max thickness 11.3% at 24.2% chord Max camber 4.6% at 29.2% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e593-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e593-il | 50,000 | 9 | 7.3 at α=-0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e593-il | 50,000 | 5 | 16.6 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e593-il | 100,000 | 9 | 25 at α=13.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e593-il | 100,000 | 5 | 36.3 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e593-il | 200,000 | 9 | 71.4 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e593-il | 200,000 | 5 | 74.2 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e593-il | 500,000 | 9 | 115.2 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e593-il | 500,000 | 5 | 113.5 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e593-il | 1,000,000 | 9 | 148.1 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e593-il | 1,000,000 | 5 | 140.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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