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.

(rae101-il) RAE 101 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE 101 airfoil Max thickness 10% at 30% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(rae100-il) RAE 100 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE 100 airfoil Max thickness 10% at 26% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(naca001064-il) NACA 0010-64		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0010-64 airfoil Max thickness 10% at 40% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(naca001035-il) NACA 0010-35		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0010-35 airfoil Max thickness 10% at 50% 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
(naca001066-il) NACA 0010-66		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0010-66 airfoil Max thickness 10% at 60% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(n63010a-il) NACA 63A010 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63-010A airfoil Max thickness 10% at 35% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(naca64a010-il) NACA 64A-010 10.0%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64A010 airfoil Max thickness 10% at 40% 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
(naca001065-il) NACA 0010-65		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0010-65 airfoil Max thickness 10% at 50% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database

Page 5 of 14     1 2 3 4 5 6 7 8 9 10 11 12 13 14     Next

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