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 | ||
(e1210-il) EPPLER 1210 AIRFOIL | Eppler E1210 general aviation airfoil Max thickness 15.9% at 21.1% chord Max camber 5.2% at 33.3% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (e1210-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e1210-il | 50,000 | 9 | 8.9 at α=0° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1210-il | 50,000 | 5 | 25.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1210-il | 100,000 | 9 | 35.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1210-il | 100,000 | 5 | 45.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1210-il | 200,000 | 9 | 60.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1210-il | 200,000 | 5 | 65.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1210-il | 500,000 | 9 | 92.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1210-il | 500,000 | 5 | 93.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1210-il | 1,000,000 | 9 | 119.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1210-il | 1,000,000 | 5 | 117.1 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||