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.

(n13-il) N-13		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	N-13 airfoil Max thickness 11.8% at 30% chord Max camber 0.1% at 95% chord Source UIUC Airfoil Coordinates Database
(n14-il) N-14		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	N-14 airfoil Max thickness 11.5% at 30% chord Max camber 0.1% at 20% chord Source UIUC Airfoil Coordinates Database
(n22-il) N-22		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	N-22 airfoil Max thickness 12.4% at 30% chord Max camber 4% at 40% chord Source UIUC Airfoil Coordinates Database
(n24-il) N-24		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	N-24 airfoil Max thickness 17% at 30% chord Max camber 5.4% at 40% chord Source UIUC Airfoil Coordinates Database
(n9-il) N-9		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	N-9 airfoil Max thickness 8.5% at 30% chord Max camber 2.7% at 40% chord Source UIUC Airfoil Coordinates Database
(naca0006-il) NACA 0006		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0006 airfoil Max thickness 6% at 30% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(naca0008-il) NACA 0008		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0008 airfoil Max thickness 8% at 30% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(naca000834-il) NACA 0008-34		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0008-34 airfoil Max thickness 8% at 40% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(naca0010-il) NACA 0010		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0010 airfoil Max thickness 10% at 30% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(naca001034-il) NACA 0010-34		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0010-34 airfoil Max thickness 10% at 40% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database

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