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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(s812-nr) NREL's S812 Airfoil | NREL HAWT airfoil S812 primary Max thickness 21% at 39.6% chord Max camber 1.6% at 77% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s812-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s812-nr | 50,000 | 9 | 17.4 at α=13.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s812-nr | 50,000 | 5 | 14.2 at α=11.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s812-nr | 100,000 | 9 | 23.9 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s812-nr | 100,000 | 5 | 25.8 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s812-nr | 200,000 | 9 | 56.2 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s812-nr | 200,000 | 5 | 59.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s812-nr | 500,000 | 9 | 92.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s812-nr | 500,000 | 5 | 87.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s812-nr | 1,000,000 | 9 | 116.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s812-nr | 1,000,000 | 5 | 105.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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