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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(s833-nr) NREL's S833 Airfoil | NREL HAWT airfoil S833 primary 18.0% Dia=1 to 3 m Re=4.0E+5 Clmax(S)=1.10 Clmax(R)=1.13 High max lift coef Max thickness 18% at 36.3% chord Max camber 2.5% at 78.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s833-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s833-nr | 50,000 | 9 | 27.5 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s833-nr | 50,000 | 5 | 23.6 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s833-nr | 100,000 | 9 | 39.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s833-nr | 100,000 | 5 | 36.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s833-nr | 200,000 | 9 | 54.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s833-nr | 200,000 | 5 | 55.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s833-nr | 500,000 | 9 | 86.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s833-nr | 500,000 | 5 | 74.3 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s833-nr | 1,000,000 | 9 | 104.1 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s833-nr | 1,000,000 | 5 | 79.9 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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