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.

(s8036-il) S8036 (16%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S8036 low Reynolds number airfoil Max thickness 16% at 36.8% chord Max camber 1.3% at 40.4% chord Source UIUC Airfoil Coordinates Database
(s819-nr) NREL's S819 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S819 primary 21.0% Dia=10 to 20 m Re=1.0E+6 Clmax(S)=1.20 Clmax(R)=1.16 Restrained max lift coef Max thickness 21.1% at 28.4% chord Max camber 1.3% at 77.3% chord Source NWTC National WInd Technology Center
(sc20412-il) NASA SC(2)-0412 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0412 airfoil (NASA TP-2969) Max thickness 12% at 37% chord Max camber 1.3% at 83% chord Source UIUC Airfoil Coordinates Database
(sc20606-il) NASA SC(2)-0606 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0606 airfoil (NASA TP-2969) Max thickness 6% at 34% chord Max camber 1.3% at 81% chord Source UIUC Airfoil Coordinates Database
(tsagi8-il) TSAGI 8% AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	TSAGI 8% airfoil Max thickness 8% at 30% chord Max camber 1.3% at 30% chord Source UIUC Airfoil Coordinates Database
(v13009-il) BOEING VERTOL V(1.95)3009-1.25 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol V(1.9)3006-1.25 rotorcraft airfoil Max thickness 9% at 30.1% chord Max camber 1.3% at 20.1% chord Source UIUC Airfoil Coordinates Database
(vr15-il) BOEING-VERTOL VR-15 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol/Dadone VR-15 transonic rotorcraft airfoil Max thickness 8% at 35% chord Max camber 1.3% at 20% chord Source UIUC Airfoil Coordinates Database
(vr8-il) BOEING-VERTOL VR-8 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol VR-8 rotorcraft airfoil Max thickness 8.2% at 35% chord Max camber 1.3% at 35% chord Source UIUC Airfoil Coordinates Database
(ag47ct02r-il) AG47ct -02f rot.		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG47ct -02f airfoil Max thickness 5% at 22.5% chord Max camber 1.2% at 33.4% chord Source UIUC Airfoil Coordinates Database
(ames03-il) NASA/AMES A-03 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/AMES/Kennelly A-03 transonic rotorcraft airfoil Max thickness 10% at 37.5% chord Max camber 1.2% at 17.5% chord Source UIUC Airfoil Coordinates Database

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