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 | ||
(ag13-il) AG13 | Drela AG13 airfoil Max thickness 5.8% at 21.3% chord Max camber 2% at 41.8% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (ag13-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ag13-il | 50,000 | 9 | 34.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag13-il | 50,000 | 5 | 35.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag13-il | 100,000 | 9 | 48.2 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag13-il | 100,000 | 5 | 47.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag13-il | 200,000 | 9 | 62.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag13-il | 200,000 | 5 | 59 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag13-il | 500,000 | 9 | 79.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag13-il | 500,000 | 5 | 75.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag13-il | 1,000,000 | 9 | 92.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag13-il | 1,000,000 | 5 | 88.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||