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.

(n63210-il) NACA 63-210 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63-210 airfoil Max thickness 10% at 35% chord Max camber 1.1% at 60% chord Source UIUC Airfoil Coordinates Database
(n63212-il) NACA 63-212 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(1)-212 airfoil Max thickness 12% at 34.9% chord Max camber 1.1% at 55% chord Source UIUC Airfoil Coordinates Database
(n63215-il) NACA 63-215 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(2)-215 airfoil Max thickness 15% at 34.9% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(n64212-il) NACA 64(1)-212		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(1)-212 airfoil Max thickness 12% at 40% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(n64215-il) NACA 64-215 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(2)-215 airfoil Max thickness 15% at 34.9% chord Max camber 1.1% at 50% 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
(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
(naca634221-il) NACA 63(4)-221		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(4)-221 airfoil Max thickness 21% at 34.9% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca64206-il) NACA 64-206		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64-206 airfoil Max thickness 6% at 40% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database

Page 24 of 164     14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33     Next

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