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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(s802-nr) NREL's S802 Airfoil | NREL HAWT airfoil S802 tip Not recommended Max thickness 11.5% at 37.9% chord Max camber 3.8% at 47.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s802-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s802-nr | 50,000 | 9 | 36.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s802-nr | 50,000 | 5 | 33.8 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s802-nr | 100,000 | 9 | 61 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s802-nr | 100,000 | 5 | 60.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s802-nr | 200,000 | 9 | 91.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s802-nr | 200,000 | 5 | 85.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s802-nr | 500,000 | 9 | 124.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s802-nr | 500,000 | 5 | 113.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s802-nr | 1,000,000 | 9 | 149.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s802-nr | 1,000,000 | 5 | 132.5 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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