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 | ||
(du861372-il) DU 86-137/25 AIRFOIL | Delft University DU 86-137/25 Airfoil Max thickness 13.6% at 41.6% chord Max camber 0.3% at 1.6% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (du861372-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| du861372-il | 50,000 | 9 | 28.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du861372-il | 50,000 | 5 | 23.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du861372-il | 100,000 | 9 | 33.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du861372-il | 100,000 | 5 | 27.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du861372-il | 200,000 | 9 | 32.8 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du861372-il | 200,000 | 5 | 35.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du861372-il | 500,000 | 9 | 46.7 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du861372-il | 500,000 | 5 | 48.9 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| du861372-il | 1,000,000 | 9 | 58.4 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| du861372-il | 1,000,000 | 5 | 59.9 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||