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 | ||
(n6409-il) NACA6409 9% | NACA 6409 Max thickness 9% at 29.3% chord Max camber 6% at 39.6% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (n6409-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| n6409-il | 50,000 | 9 | 27.1 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n6409-il | 50,000 | 5 | 36 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n6409-il | 100,000 | 9 | 61.6 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n6409-il | 100,000 | 5 | 63.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n6409-il | 200,000 | 9 | 87.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n6409-il | 200,000 | 5 | 87.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n6409-il | 500,000 | 9 | 122.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n6409-il | 500,000 | 5 | 118.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n6409-il | 1,000,000 | 9 | 151 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n6409-il | 1,000,000 | 5 | 144.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||