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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(s825-nr) NREL's S825 Airfoil | NREL HAWT airfoil S825 primary 17.0% Dia=20 to 40 m Re=2.0E+6 Clmax(S)=1.44 Clmax(R)=1.37 High max lift coef Max thickness 17.1% at 29.9% chord Max camber 3.9% at 65.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s825-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s825-nr | 50,000 | 9 | 29.3 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s825-nr | 50,000 | 5 | 32.2 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s825-nr | 100,000 | 9 | 50.3 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s825-nr | 100,000 | 5 | 52.8 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s825-nr | 200,000 | 9 | 70.1 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s825-nr | 200,000 | 5 | 70.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s825-nr | 500,000 | 9 | 97.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s825-nr | 500,000 | 5 | 94 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s825-nr | 1,000,000 | 9 | 118.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s825-nr | 1,000,000 | 5 | 111 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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