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 | ||
(dae11-il) DAE-11 AIRFOIL | Drela DAE11 low Reynolds number airfoil Max thickness 12.8% at 32.8% chord Max camber 6.6% at 44.4% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (dae11-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| dae11-il | 50,000 | 9 | 6.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae11-il | 50,000 | 5 | 13.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae11-il | 100,000 | 9 | 31.3 at α=13° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae11-il | 100,000 | 5 | 32.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae11-il | 200,000 | 9 | 79 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae11-il | 200,000 | 5 | 83.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae11-il | 500,000 | 9 | 135.8 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae11-il | 500,000 | 5 | 132.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae11-il | 1,000,000 | 9 | 177.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae11-il | 1,000,000 | 5 | 165 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||