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.

(naca16015-il) NACA 16-015		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 16-015 airfoil Max thickness 15% at 50% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(naca16018-il) NACA 16-018		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 16-018 airfoil Max thickness 18% at 50% 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
(naca16009-il) NACA 16009		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 16009 airfoil Max thickness 9% at 50% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(n2h15-il) NACA 2-H-15 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 2-H-15 rotorcraft airfoil Max thickness 14.7% at 40% chord Max camber 4.5% at 40% chord Source UIUC Airfoil Coordinates Database
(naca2411-il) NACA 2.5411		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 2411 airfoil Max thickness 11% at 29.5% chord Max camber 2.5% at 39.6% chord Source UIUC Airfoil Coordinates Database
(naca22112-jf) NACA 22112		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file
	NACA 22112 5 digit reflex airfoil Max thickness 12% at 29.5% chord Max camber 0.8% at 9.6% chord Source Javafoil generated
(naca23012-il) NACA 23012 12%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 23012 airfoil Max thickness 12% at 29.8% chord Max camber 1.8% at 12.7% chord Source UIUC Airfoil Coordinates Database
(naca23015-il) NACA 23015		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 23015 airfoil Max thickness 15% at 30% chord Max camber 1.8% at 15% chord Source UIUC Airfoil Coordinates Database
(naca23018-il) NACA 23018		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 23018 airfoil Max thickness 18% at 30% chord Max camber 1.8% at 15% chord Source UIUC Airfoil Coordinates Database

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