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 | ||
(e59-il) EPPLER 59 AIRFOIL | Eppler E59 low Reynolds number airfoil Max thickness 5.6% at 25% chord Max camber 5.2% at 50% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (e59-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e59-il | 50,000 | 9 | 43.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e59-il | 50,000 | 5 | 46.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e59-il | 100,000 | 9 | 69.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e59-il | 100,000 | 5 | 70.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e59-il | 200,000 | 9 | 103.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e59-il | 200,000 | 5 | 99.6 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e59-il | 500,000 | 9 | 155.6 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e59-il | 500,000 | 5 | 119.3 at α=0.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e59-il | 1,000,000 | 9 | 188.8 at α=0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e59-il | 1,000,000 | 5 | 108.8 at α=-1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||