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.

(s4320-il) S4320		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S4320 low Reynolds number airfoil Max thickness 9.4% at 26.8% chord Max camber 4.5% at 40.2% chord Source UIUC Airfoil Coordinates Database
(usa41-il) USA 41 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-41 airfoil Max thickness 6.6% at 30% chord Max camber 4.5% at 40% chord Source UIUC Airfoil Coordinates Database
(goe723-il) GOE 723 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 723 airfoil Max thickness 11.6% at 29.7% chord Max camber 4.5% at 49.7% chord Source UIUC Airfoil Coordinates Database
(isa960-il) I.S.A. 960		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	I.S.A. 960 airfoil Max thickness 9.5% at 30% chord Max camber 4.5% at 40% chord Source UIUC Airfoil Coordinates Database
(e598-il) EPPLER 598 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E598 airfoil Max thickness 11.1% at 24.2% chord Max camber 4.5% at 34.4% chord Source UIUC Airfoil Coordinates Database
(defcnd1-il) DEFIANT CANARD BL20 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rutan DEFIANT canard BL20 airfoil Max thickness 20.9% at 28.6% chord Max camber 4.5% at 36.1% chord Source UIUC Airfoil Coordinates Database
(n11h9-il) NACA 11-H-09 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 11-H-9 rotorcraft airfoil Max thickness 9% at 40.2% chord Max camber 4.5% at 30% chord Source UIUC Airfoil Coordinates Database
(e584-il) EPPLER 584 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E584 sailplane airfoil Max thickness 16.6% at 38.3% chord Max camber 4.5% at 38.3% chord Source UIUC Airfoil Coordinates Database
(goe425-il) GOE 425 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 425 airfoil Max thickness 16% at 29.3% chord Max camber 4.5% at 39.3% chord Source UIUC Airfoil Coordinates Database
(e583-il) EPPLER 583 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E583 sailplane airfoil Max thickness 16.5% at 38% chord Max camber 4.5% at 38% chord Source UIUC Airfoil Coordinates Database

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