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.

(naca4415-il) NACA 4415		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 4415 airfoil Max thickness 15% at 30.9% chord Max camber 4% at 40.2% chord Source UIUC Airfoil Coordinates Database
(naca4418-il) NACA 4418		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 4418 airfoil Max thickness 18% at 30% chord Max camber 4% at 40% chord Source UIUC Airfoil Coordinates Database
(naca4421-il) NACA 4421		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 4421 airfoil Max thickness 21% at 30% chord Max camber 4% at 40% chord Source UIUC Airfoil Coordinates Database
(naca4424-il) NACA 4424		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 4424 airfoil Max thickness 24% at 29.4% chord Max camber 4% at 40% chord Source UIUC Airfoil Coordinates Database
(naca63206-il) NACA 63-206		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63-206 airfoil Max thickness 6% at 35% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca63209-il) NACA 63-209		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63-209 airfoil Max thickness 9% at 35% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca632615-il) NACA 63(2)-615		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(2)-615 airfoil Max thickness 15% at 34.8% chord Max camber 3.3% at 50% chord Source UIUC Airfoil Coordinates Database
(naca632a015-il) NACA 63(2)A-015		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(2)A-015 airfoil Max thickness 15% at 37.1% chord Max camber 1.7% at 14.6% chord Source UIUC Airfoil Coordinates Database
(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
(naca633218-il) NACA 63(3)-218		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(3)-218 airfoil Max thickness 18% at 34.9% chord Max camber 1.1% at 24.9% chord Source UIUC Airfoil Coordinates Database

Page 13 of 19     0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19     Next

Please see the source web site or designer for any license conditions.