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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(s822-nr) NREL's S822 Airfoil | NREL HAWT airfoil S822 tip 16.0% Dia=2 to 10 m Re=6.0E+5 Clmax(S)=1.00 Clmax(R)=0.98 Restrained max lift coef Max thickness 16% at 39.2% chord Max camber 1.8% at 59.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s822-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s822-nr | 50,000 | 9 | 27.7 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s822-nr | 50,000 | 5 | 23.7 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s822-nr | 100,000 | 9 | 42.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s822-nr | 100,000 | 5 | 39.8 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s822-nr | 200,000 | 9 | 68.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s822-nr | 200,000 | 5 | 60.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s822-nr | 500,000 | 9 | 94.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s822-nr | 500,000 | 5 | 85.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s822-nr | 1,000,000 | 9 | 117.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s822-nr | 1,000,000 | 5 | 96.9 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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