Airfoil database search (Symmetrical)

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.

(naca633018-il) NACA 63(3)-018		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(3)-018 airfoil Max thickness 18% at 33.9% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(naca66-018-il) NACA 66-018		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66-018 airfoil Max thickness 18% at 45% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(naca0018-il) NACA 0018		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0018 airfoil Max thickness 18% at 30% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(e838-il) EPPLER E838 HYDROFOIL AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E838 hydrofoil Max thickness 18.4% at 37.2% chord Max camber 0% at 46.5% chord Source UIUC Airfoil Coordinates Database
(us1000root-il) US1000ROOT		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Great Planes R/C Ultra-Sport 1000 airfoil Max thickness 18.6% at 27.1% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(goe460-il) GOE 460 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 460 airfoil Max thickness 20.5% at 30% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(naca16021-il) NACA 16-021		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 16-021 airfoil Max thickness 21% at 50% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(joukowsk0021-jf) Joukovsky f=0% t=21%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file
	Joukowski 21% symmetrical airfoil Max thickness 21% at 26.6% chord Max camber 0% at 0% chord Source Javafoil generated
(naca0021-il) NACA 0021		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0021 airfoil Max thickness 21% at 30% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(goe775-il) GOE 775 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 775 airfoil Max thickness 21% at 30% chord Max camber 0% at 1.3% chord Source UIUC Airfoil Coordinates Database

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