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.

(ht22-il) HT22		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela HT22 airfoil Max thickness 5.1% at 19.1% chord Max camber 1.1% at 22.7% chord Source UIUC Airfoil Coordinates Database
(naca671215-il) NACA 67		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 67 Max thickness 15% at 50% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca664221-il) NACA 66(4)-221		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66(4)-221 airfoil Max thickness 21% at 45% chord Max camber 1.1% 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
(rc08b3-il) NASA/LANGLEY RC-08(B)3 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley RC-08(B)3 rotorcraft airfoil Max thickness 8% at 37.8% chord Max camber 1.1% at 34.1% chord Source UIUC Airfoil Coordinates Database
(e485-il) EPPLER 485 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E485 tailplane airfoil Max thickness 12.5% at 31.8% chord Max camber 1.1% at 27.1% chord Source UIUC Airfoil Coordinates Database
(naca663218-il) NACA 66(3)-218		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66(3)-218 airfoil Max thickness 18% at 45% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca642215-il) NACA 64(2)-215		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
(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
(naca662215-il) NACA 66(2)-215		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66(2)-215 airfoil Max thickness 15% at 45% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database

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