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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(s830-nr) NREL's S830 Airfoil | NREL HAWT airfoil S830 primary 21.0% Dia=40 to 50 m Re=4.0E+6 Clmax(S)=1.60 Clmax(R)=1.57 High max lift coef Max thickness 21% at 38.4% chord Max camber 4.4% at 70.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s830-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s830-nr | 50,000 | 9 | 4.2 at α=12.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s830-nr | 50,000 | 5 | 10.8 at α=15.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s830-nr | 100,000 | 9 | 17.7 at α=14° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s830-nr | 100,000 | 5 | 34.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s830-nr | 200,000 | 9 | 61.1 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s830-nr | 200,000 | 5 | 66.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s830-nr | 500,000 | 9 | 95.2 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s830-nr | 500,000 | 5 | 94 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s830-nr | 1,000,000 | 9 | 117.8 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s830-nr | 1,000,000 | 5 | 115.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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