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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(s801-nr) NREL's S801 Airfoil | NREL HAWT airfoil S801 primary 13.5% Not recommended Max thickness 13.5% at 37.8% chord Max camber 3.7% at 47.1% chord | Remove Airfoil details Airfoil plotter |
(s815-nr) NREL's S815 Airfoil | NREL HAWT airfoil S815 root 26.0% Dia=20 to 30 m Re=1.2E+6 Clmax(S)=1.46 Clmax(R)=1.40 High max lift coef Max thickness 26.2% at 25.7% chord Max camber 2.9% at 77.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s801-nr,s815-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s801-nr | 50,000 | 9 | 31.7 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s801-nr | 50,000 | 5 | 27.1 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s801-nr | 100,000 | 9 | 52.1 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s801-nr | 100,000 | 5 | 52.2 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s801-nr | 200,000 | 9 | 85.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s801-nr | 200,000 | 5 | 80.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s801-nr | 500,000 | 9 | 118.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s801-nr | 500,000 | 5 | 112 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s801-nr | 1,000,000 | 9 | 147.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s801-nr | 1,000,000 | 5 | 133.2 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s815-nr | 50,000 | 9 | 3.2 at α=-1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s815-nr | 50,000 | 5 | 9 at α=15.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s815-nr | 100,000 | 9 | 26.2 at α=12.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s815-nr | 100,000 | 5 | 36 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s815-nr | 200,000 | 9 | 54.4 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s815-nr | 200,000 | 5 | 54.8 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s815-nr | 500,000 | 9 | 79.5 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s815-nr | 500,000 | 5 | 75.9 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s815-nr | 1,000,000 | 9 | 99.4 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s815-nr | 1,000,000 | 5 | 91.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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