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 | ||
(e558-il) EPPLER 558 AIRFOIL | Eppler E558 general aviation airfoil Max thickness 16% at 26.4% chord Max camber 3.8% at 49.3% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (e558-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e558-il | 50,000 | 9 | 9.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e558-il | 50,000 | 5 | 29.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e558-il | 100,000 | 9 | 41.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e558-il | 100,000 | 5 | 50.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e558-il | 200,000 | 9 | 67.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e558-il | 200,000 | 5 | 70.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e558-il | 500,000 | 9 | 100.1 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e558-il | 500,000 | 5 | 99.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e558-il | 1,000,000 | 9 | 127 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e558-il | 1,000,000 | 5 | 120.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||