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.

(naca63a210-il) NACA 63A210		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63A210 airfoil Max thickness 10% at 34.9% chord Max camber 1.3% at 50% chord Source UIUC Airfoil Coordinates Database
(naca64210-il) NACA 64-210		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64-210 airfoil Max thickness 10% at 40% chord Max camber 1.1% at 50% 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
(naca64a210-il) NACA 64A210		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64A210 airfoil Max thickness 10% at 40% chord Max camber 1.3% at 50% chord Source UIUC Airfoil Coordinates Database
(naca64a410-il) NACA 64A410		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64A410 airfoil Max thickness 10% at 39.9% chord Max camber 2.7% at 50% chord Source UIUC Airfoil Coordinates Database
(naca65210-il) NACA 65-210		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65-210 airfoil Max thickness 10% at 40% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca65410-il) NACA 65-410		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65-410 airfoil Max thickness 10% at 39.9% chord Max camber 2.2% at 50% chord Source UIUC Airfoil Coordinates Database
(naca66210-il) NACA 66-210		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66-210 airfoil Max thickness 10% at 45% chord Max camber 1.1% at 50% 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
(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

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