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 | ||
(dae21-il) DAE-21 AIRFOIL | Drela DAE21 low Reynolds number airfoil Max thickness 11.8% at 32% chord Max camber 6.6% at 43.7% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (dae21-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| dae21-il | 50,000 | 9 | 7.1 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae21-il | 50,000 | 5 | 17.1 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae21-il | 100,000 | 9 | 45.9 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae21-il | 100,000 | 5 | 50.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae21-il | 200,000 | 9 | 86.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae21-il | 200,000 | 5 | 88.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae21-il | 500,000 | 9 | 136.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae21-il | 500,000 | 5 | 130.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae21-il | 1,000,000 | 9 | 173.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae21-il | 1,000,000 | 5 | 158.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||