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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(s804-nr) NREL's S804 Airfoil | NREL HAWT airfoil S804 root Not recommended Max thickness 17.9% at 26.7% chord Max camber 4.2% at 39.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s804-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s804-nr | 50,000 | 9 | 4.8 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s804-nr | 50,000 | 5 | 22.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s804-nr | 100,000 | 9 | 28.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s804-nr | 100,000 | 5 | 45.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s804-nr | 200,000 | 9 | 58.2 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s804-nr | 200,000 | 5 | 67.9 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s804-nr | 500,000 | 9 | 98.1 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s804-nr | 500,000 | 5 | 98.6 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s804-nr | 1,000,000 | 9 | 128 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s804-nr | 1,000,000 | 5 | 125.5 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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