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 | ||
(s823-nr) NREL's S823 Airfoil | NREL HAWT airfoil S823 root 21.0% Dia=2 to 10 m Re=4.0E+5 Clmax(S)=1.20 Clmax(R)=1.16 Restrained max lift coef Max thickness 21.2% at 24.3% chord Max camber 2.4% at 70.5% chord | Remove Airfoil details Airfoil plotter |
Drawing Options
Polars for (s823-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s823-nr | 50,000 | 9 | 20.9 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s823-nr | 50,000 | 5 | 20.4 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s823-nr | 100,000 | 9 | 42.3 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s823-nr | 100,000 | 5 | 43.2 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s823-nr | 200,000 | 9 | 62.5 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s823-nr | 200,000 | 5 | 60 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s823-nr | 500,000 | 9 | 86.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s823-nr | 500,000 | 5 | 77.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s823-nr | 1,000,000 | 9 | 101.5 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s823-nr | 1,000,000 | 5 | 87.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||