Airfoil Tools
Search 1638 airfoils

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Your Reynold number range is 50,000 to 1,000,000. (set)

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.

(naca642415-il) NACA 64(2)-415		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(2)-415 airfoil Max thickness 15% at 34.9% chord Max camber 2.2% at 50% chord Source UIUC Airfoil Coordinates Database
(naca643218-il) NACA 64(3)-218		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(3)-218 airfoil Max thickness 18% at 34.9% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca643418-il) NACA 64(3)-418		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(3)-418 airfoil Max thickness 17.9% at 34.8% chord Max camber 2.2% at 50% chord Source UIUC Airfoil Coordinates Database
(naca643618-il) NACA 64(3)-618		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(3)-618 airfoil Max thickness 17.9% at 34.7% chord Max camber 3.3% at 50% chord Source UIUC Airfoil Coordinates Database
(naca644221-il) NACA 64(4)-221		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(4)-221 airfoil Max thickness 21% at 34.9% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database

(naca644421-il) NACA 64(4)-421		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(4)-421 airfoil Max thickness 20.9% at 34.8% chord Max camber 2.2% at 50% chord Source UIUC Airfoil Coordinates Database
(n64008a-il) NACA 64-008A AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64-008A airfoil Max thickness 8% at 40% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(n64012a-il) NACA 64-012A AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(1)-012A airfoil Max thickness 12% at 40% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(n64108-il) NACA 64-108 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64-108 airfoil Max thickness 8% at 40% chord Max camber 0.6% at 50% chord Source UIUC Airfoil Coordinates Database
(n64110-il) NACA 64-110 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64-110 airfoil Max thickness 10% at 40% chord Max camber 0.6% at 50% chord Source UIUC Airfoil Coordinates Database