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 | ||
(n5h20-il) NACA 5-H-20 AIRFOIL | NACA 5-H-20 rotorcraft airfoil Max thickness 19.9% at 40% chord Max camber 4.5% at 40% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (n5h20-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| n5h20-il | 50,000 | 9 | 3.5 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n5h20-il | 50,000 | 5 | 7.1 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n5h20-il | 100,000 | 9 | 17 at α=15.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n5h20-il | 100,000 | 5 | 14.8 at α=14.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n5h20-il | 200,000 | 9 | 25.4 at α=13° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n5h20-il | 200,000 | 5 | 34.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n5h20-il | 500,000 | 9 | 78.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n5h20-il | 500,000 | 5 | 56.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n5h20-il | 1,000,000 | 9 | 85.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n5h20-il | 1,000,000 | 5 | 75.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||