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 | ||
(nacam3-il) NACA M3 | NACA M3 airfoil Max thickness 11.9% at 30% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (nacam3-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| nacam3-il | 50,000 | 9 | 27.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam3-il | 50,000 | 5 | 26.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam3-il | 100,000 | 9 | 37.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam3-il | 100,000 | 5 | 34.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam3-il | 200,000 | 9 | 45.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam3-il | 200,000 | 5 | 42.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam3-il | 500,000 | 9 | 54.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam3-il | 500,000 | 5 | 56.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacam3-il | 1,000,000 | 9 | 66.9 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacam3-il | 1,000,000 | 5 | 69.5 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||