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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(s811-nr) NREL's S811 Airfoil | NREL HAWT airfoil S811 root Max thickness 26.3% at 27.4% chord Max camber 1.7% at 76.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s811-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s811-nr | 50,000 | 9 | 6.1 at α=-0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s811-nr | 50,000 | 5 | 7.5 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s811-nr | 100,000 | 9 | 12.8 at α=15° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s811-nr | 100,000 | 5 | 28.4 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s811-nr | 200,000 | 9 | 48.8 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s811-nr | 200,000 | 5 | 52.3 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s811-nr | 500,000 | 9 | 79.1 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s811-nr | 500,000 | 5 | 76 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s811-nr | 1,000,000 | 9 | 99.5 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s811-nr | 1,000,000 | 5 | 90.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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