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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(s832-nr) NREL's S832 Airfoil | NREL HAWT airfoil S832 Max thickness 14.9% at 44% chord Max camber 5.3% at 44% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s832-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s832-nr | 50,000 | 9 | 19.8 at α=13.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s832-nr | 50,000 | 5 | 16 at α=13.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s832-nr | 100,000 | 9 | 26.4 at α=12.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s832-nr | 100,000 | 5 | 25.2 at α=11.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s832-nr | 200,000 | 9 | 54.7 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s832-nr | 200,000 | 5 | 67.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s832-nr | 500,000 | 9 | 126 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s832-nr | 500,000 | 5 | 118.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s832-nr | 1,000,000 | 9 | 163.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s832-nr | 1,000,000 | 5 | 151.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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