Airfoil Tools
Search 1638 airfoils

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Your Reynold number range is 50,000 to 1,000,000. (set)

Airfoil database search

Search the 1638 airfoils available in the databases filtering by name, thickness and camber. Click on an airfoil image to display a larger preview picture. There are links to the original airfoil source and dat file and the details page with polar diagrams for a range of Reynolds numbers.

(s8065-il) S8065 (11% version of S8064)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig airfoil for Q-40 pylon racing (11%). Max thickness 11% at 37.8% chord Max camber 1.1% at 56.3% chord Source UIUC Airfoil Coordinates Database
(s8066-il) S8066 (10% version of S8065 w/ lower surface aerodynamically similar)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig airfoil for Q-40 pylon racing (10%). Max thickness 10% at 37.7% chord Max camber 0.8% at 56.3% chord Source UIUC Airfoil Coordinates Database
(s806a-nr) NREL's S806A Airfoil (modified line 35)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S806A tip Max thickness 11.5% at 45% chord Max camber 2.8% at 45% chord Source NWTC National WInd Technology Center
(s807-nr) NREL's S807 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S807 root Max thickness 18% at 28.7% chord Max camber 1.9% at 78.3% chord Source NWTC National WInd Technology Center
(s808-nr) NREL's S808 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S808 root Max thickness 21% at 24.4% chord Max camber 2.4% at 72.9% chord Source NWTC National WInd Technology Center

(s809-nr) NREL's S809 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S809 primary 21.0% Re=2.0E+6 Clmax(S)=1.00 Restrained max lift coef Max thickness 21% at 39.5% chord Max camber 1% at 82.3% chord Source NWTC National WInd Technology Center
(s810-nr) NREL's S810 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S810 tip Max thickness 18% at 44.2% chord Max camber 0.9% at 10.9% chord Source NWTC National WInd Technology Center
(s811-nr) NREL's S811 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S811 root Max thickness 26.3% at 27.4% chord Max camber 1.7% at 76.4% chord Source NWTC National WInd Technology Center
(s812-nr) NREL's S812 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S812 primary Max thickness 21% at 39.6% chord Max camber 1.6% at 77% chord Source NWTC National WInd Technology Center
(s813-nr) NREL's S813 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S813 tip Max thickness 16% at 40.4% chord Max camber 2.3% at 54.4% chord Source NWTC National WInd Technology Center