Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
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(s809-nr) NREL's S809 Airfoil | NREL HAWT airfoil S809 primary 21.0% Re=2.0E+6 Clmax(S)=1.00 Restrained max lift coef Max thickness 21% at 39.5% chord Max camber 1% at 82.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s809-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s809-nr | 50,000 | 9 | 15.5 at α=12.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s809-nr | 50,000 | 5 | 13.9 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s809-nr | 100,000 | 9 | 23.4 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s809-nr | 100,000 | 5 | 26.8 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s809-nr | 200,000 | 9 | 51.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s809-nr | 200,000 | 5 | 53.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s809-nr | 500,000 | 9 | 81.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s809-nr | 500,000 | 5 | 75.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s809-nr | 1,000,000 | 9 | 100.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s809-nr | 1,000,000 | 5 | 89.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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