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.

(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
(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
(naca0008-il) NACA 0008		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0008 airfoil Max thickness 8% at 30% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(naca000834-il) NACA 0008-34		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0008-34 airfoil Max thickness 8% at 40% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(naca1408-il) NACA 1408		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 1408 airfoil Max thickness 8% at 30% chord Max camber 1% at 40% chord Source UIUC Airfoil Coordinates Database
(naca2408-il) NACA 2408		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 2408 airfoil Max thickness 8% at 29.9% chord Max camber 2% at 40% chord Source UIUC Airfoil Coordinates Database
(naca64208-il) NACA 64-208		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64-208 airfoil Max thickness 8% at 40% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(rc0864c-il) NASA/LANGLEY RC08-64C AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley 08-64C rotorcraft airfoil Max thickness 8% at 40% chord Max camber 1% at 35% 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
(rc08n1-il) NASA/LANGLEY RC-08(N)1 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(N)1 rotorcraft airfoil Max thickness 8% at 37.5% chord Max camber 1.6% at 25% chord Source UIUC Airfoil Coordinates Database

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