Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
| Open full size plan in new window | Open paginated plan in new window | |
| Download PDF file | SVG image as text file | |
| Clear all | ||
(e557-il) EPPLER 557 AIRFOIL | Eppler E557 general aviation airfoil Max thickness 16% at 30.2% chord Max camber 3.7% at 60.8% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (e557-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e557-il | 50,000 | 9 | 25.4 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e557-il | 50,000 | 5 | 32.3 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e557-il | 100,000 | 9 | 53.7 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e557-il | 100,000 | 5 | 54.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e557-il | 200,000 | 9 | 75 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e557-il | 200,000 | 5 | 73.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e557-il | 500,000 | 9 | 102.1 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e557-il | 500,000 | 5 | 95.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e557-il | 1,000,000 | 9 | 122.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e557-il | 1,000,000 | 5 | 110.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||