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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(e554-il) EPPLER 554 AIRFOIL | Eppler E554 general aviation airfoil Max thickness 18.2% at 31.8% chord Max camber 2.7% at 56.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e554-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e554-il | 50,000 | 9 | 4.8 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e554-il | 50,000 | 5 | 18.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e554-il | 100,000 | 9 | 36.4 at α=12.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e554-il | 100,000 | 5 | 46.2 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e554-il | 200,000 | 9 | 69 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e554-il | 200,000 | 5 | 70.2 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e554-il | 500,000 | 9 | 103.2 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e554-il | 500,000 | 5 | 98.8 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e554-il | 1,000,000 | 9 | 127.8 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e554-il | 1,000,000 | 5 | 118.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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