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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(s831-nr) NREL's S831 Airfoil | NREL HAWT airfoil S831 tip 18.0% Dia=40 to 50 m Re=3.5E+6 Clmax(S)=1.50 Clmax(R)=1.48 High max lift coef Max thickness 18% at 44.2% chord Max camber 5% at 53.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s831-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s831-nr | 50,000 | 9 | 17.2 at α=13.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s831-nr | 50,000 | 5 | 14.2 at α=13.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s831-nr | 100,000 | 9 | 21.8 at α=13° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s831-nr | 100,000 | 5 | 21.2 at α=12.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s831-nr | 200,000 | 9 | 36.7 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s831-nr | 200,000 | 5 | 47 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s831-nr | 500,000 | 9 | 113.9 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s831-nr | 500,000 | 5 | 112.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s831-nr | 1,000,000 | 9 | 152.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s831-nr | 1,000,000 | 5 | 147.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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