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 | ||
(e502-il) EPPLER 502 AIRFOIL | Eppler E502 general purpose airfoil Max thickness 15.6% at 42.1% chord Max camber 1.5% at 32.3% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (e502-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e502-il | 50,000 | 9 | 24.6 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e502-il | 50,000 | 5 | 21 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e502-il | 100,000 | 9 | 45.6 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e502-il | 100,000 | 5 | 36.2 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e502-il | 200,000 | 9 | 58.8 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e502-il | 200,000 | 5 | 58 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e502-il | 500,000 | 9 | 88 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e502-il | 500,000 | 5 | 80 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e502-il | 1,000,000 | 9 | 106.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e502-il | 1,000,000 | 5 | 90.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||