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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(s805a-nr) NREL's S805A Airfoil | NREL HAWT airfoil S805A primary Max thickness 13.5% at 40% chord Max camber 2.1% at 35% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s805a-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s805a-nr | 50,000 | 9 | 30.1 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s805a-nr | 50,000 | 5 | 27.1 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s805a-nr | 100,000 | 9 | 50.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s805a-nr | 100,000 | 5 | 50.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s805a-nr | 200,000 | 9 | 75.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s805a-nr | 200,000 | 5 | 67 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s805a-nr | 500,000 | 9 | 96.9 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s805a-nr | 500,000 | 5 | 89.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s805a-nr | 1,000,000 | 9 | 117.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s805a-nr | 1,000,000 | 5 | 103.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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