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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(s810-nr) NREL's S810 Airfoil | NREL HAWT airfoil S810 tip Max thickness 18% at 44.2% chord Max camber 0.9% at 10.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s810-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s810-nr | 50,000 | 9 | 20.7 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s810-nr | 50,000 | 5 | 16.5 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s810-nr | 100,000 | 9 | 24.9 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s810-nr | 100,000 | 5 | 27.1 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s810-nr | 200,000 | 9 | 50 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s810-nr | 200,000 | 5 | 52.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s810-nr | 500,000 | 9 | 83.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s810-nr | 500,000 | 5 | 77.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s810-nr | 1,000,000 | 9 | 105.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s810-nr | 1,000,000 | 5 | 92.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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