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 | ||
(e340-il) EPPLER 340 AIRFOIL | Eppler E340 flying wing airfoil Max thickness 13.7% at 28.8% chord Max camber 2.6% at 19.7% chord | Remove Airfoil details Airfoil plotter |
(miley-il) MILEY M06-13-128 | Miley MO6-13-128 airfoil Max thickness 12.9% at 35% chord Max camber 4.9% at 35% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (e340-il,miley-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e340-il | 50,000 | 9 | 13.6 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e340-il | 50,000 | 5 | 22.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e340-il | 100,000 | 9 | 28.4 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e340-il | 100,000 | 5 | 42.1 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e340-il | 200,000 | 9 | 58.7 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e340-il | 200,000 | 5 | 57 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e340-il | 500,000 | 9 | 80.3 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e340-il | 500,000 | 5 | 74.3 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e340-il | 1,000,000 | 9 | 94.2 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e340-il | 1,000,000 | 5 | 93.7 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| miley-il | 50,000 | 9 | 5.8 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| miley-il | 50,000 | 5 | 11 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| miley-il | 100,000 | 9 | 23.5 at α=13° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| miley-il | 100,000 | 5 | 23.2 at α=12.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| miley-il | 200,000 | 9 | 61.2 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| miley-il | 200,000 | 5 | 62.8 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| miley-il | 500,000 | 9 | 122.8 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| miley-il | 500,000 | 5 | 121.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| miley-il | 1,000,000 | 9 | 168 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| miley-il | 1,000,000 | 5 | 157.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||