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 | ||
(s818-nr) NREL's S818 Airfoil | NREL HAWT airfoil S818 root 24.0% Dia=30 to 50 m Re=2.5E+6 Clmax(S)=1.68 Clmax(R)=1.61 Restrained max lift coef Max thickness 24% at 30.9% chord Max camber 3.3% at 74.2% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (s818-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s818-nr | 50,000 | 9 | 6.8 at α=-0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s818-nr | 50,000 | 5 | 11.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s818-nr | 100,000 | 9 | 16.7 at α=14.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s818-nr | 100,000 | 5 | 39.6 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s818-nr | 200,000 | 9 | 57.7 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s818-nr | 200,000 | 5 | 58.8 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s818-nr | 500,000 | 9 | 83.4 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s818-nr | 500,000 | 5 | 81.9 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s818-nr | 1,000,000 | 9 | 105.9 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s818-nr | 1,000,000 | 5 | 101.1 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||