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 | ||
(naca22112-jf) NACA 22112 | NACA 22112 5 digit reflex airfoil Max thickness 12% at 29.5% chord Max camber 0.8% at 9.6% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (naca22112-jf)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca22112-jf | 50,000 | 9 | 23.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca22112-jf | 50,000 | 5 | 26.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca22112-jf | 100,000 | 9 | 33.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca22112-jf | 100,000 | 5 | 36.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca22112-jf | 200,000 | 9 | 45.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca22112-jf | 200,000 | 5 | 49.5 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca22112-jf | 500,000 | 9 | 67.7 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca22112-jf | 500,000 | 5 | 71.6 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca22112-jf | 1,000,000 | 9 | 89.4 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca22112-jf | 1,000,000 | 5 | 89.4 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||