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 | ||
(e360-il) EPPLER 360 AIRFOIL | Eppler E360 rotorcraft airfoil Max thickness 12.2% at 36.9% chord Max camber 1.6% at 27.2% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (e360-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e360-il | 50,000 | 9 | 30.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e360-il | 50,000 | 5 | 31.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e360-il | 100,000 | 9 | 47.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e360-il | 100,000 | 5 | 46 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e360-il | 200,000 | 9 | 63.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e360-il | 200,000 | 5 | 52.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e360-il | 500,000 | 9 | 69.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e360-il | 500,000 | 5 | 69 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e360-il | 1,000,000 | 9 | 86 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e360-il | 1,000,000 | 5 | 84 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||