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 | ||
(eh2012-il) EH 2.0/12 | John Yost EH 2.0/12 for tailless R/C aircraft Max thickness 12% at 28.7% chord Max camber 2% at 25.9% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (eh2012-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| eh2012-il | 50,000 | 9 | 18 at α=12.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh2012-il | 50,000 | 5 | 28.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh2012-il | 100,000 | 9 | 42.5 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh2012-il | 100,000 | 5 | 45.9 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh2012-il | 200,000 | 9 | 61.8 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh2012-il | 200,000 | 5 | 63.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh2012-il | 500,000 | 9 | 89.3 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh2012-il | 500,000 | 5 | 85.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| eh2012-il | 1,000,000 | 9 | 106.5 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| eh2012-il | 1,000,000 | 5 | 97.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||