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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(s827-nr) NREL's S827 Airfoil | NREL HAWT airfoil S827 primary 21.0% Dia=40 to 50 m Re=4.0E+6 Clmax(S)=1.00 Clmax(R)=0.99 Restrained max lift coef Max thickness 21% at 44.9% chord Max camber 2.2% at 68% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s827-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s827-nr | 50,000 | 9 | 16.5 at α=12.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s827-nr | 50,000 | 5 | 14 at α=11.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s827-nr | 100,000 | 9 | 20.4 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s827-nr | 100,000 | 5 | 21.3 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s827-nr | 200,000 | 9 | 35.6 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s827-nr | 200,000 | 5 | 35 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s827-nr | 500,000 | 9 | 84.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s827-nr | 500,000 | 5 | 81.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s827-nr | 1,000,000 | 9 | 121.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s827-nr | 1,000,000 | 5 | 109.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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