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 | ||
(m8-il) NACA M8 AIRFOIL | NACA/Munk M-8 airfoil Max thickness 11.7% at 15% chord Max camber 8% at 30% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (m8-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| m8-il | 50,000 | 9 | 8.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m8-il | 50,000 | 5 | 26.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m8-il | 100,000 | 9 | 40.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m8-il | 100,000 | 5 | 46.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m8-il | 200,000 | 9 | 60.2 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m8-il | 200,000 | 5 | 62.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m8-il | 500,000 | 9 | 83 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m8-il | 500,000 | 5 | 79.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m8-il | 1,000,000 | 9 | 96.6 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m8-il | 1,000,000 | 5 | 99.1 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||