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 | ||
(n8h12-il) NACA 8-H-12 AIRFOIL | NACA 8-H-12 rotorcraft airfoil Max thickness 12% at 30% chord Max camber 3.5% at 30% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (n8h12-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| n8h12-il | 50,000 | 9 | 8 at α=-0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n8h12-il | 50,000 | 5 | 18.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n8h12-il | 100,000 | 9 | 45.6 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n8h12-il | 100,000 | 5 | 48 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n8h12-il | 200,000 | 9 | 72 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n8h12-il | 200,000 | 5 | 71.2 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n8h12-il | 500,000 | 9 | 104.2 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n8h12-il | 500,000 | 5 | 98.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n8h12-il | 1,000,000 | 9 | 128.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n8h12-il | 1,000,000 | 5 | 118.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||