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.

(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
(s2055-il) S2055		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S2055 low Reynolds number airfoil Max thickness 8% at 34.8% chord Max camber 1.4% at 44.6% chord Source UIUC Airfoil Coordinates Database
(s2060-il) S2060 8%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S2060 low Reynolds number airfoil Max thickness 8% at 30.2% chord Max camber 1.6% at 49.7% chord Source UIUC Airfoil Coordinates Database
(s2062-il) S2062 8%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S2062 low Reynolds number airfoil Max thickness 8% at 30.1% chord Max camber 1.5% at 49.6% chord Source UIUC Airfoil Coordinates Database
(s4083-il) S4083 (8%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S4083 low Reynolds number airfoil Max thickness 8% at 22.5% chord Max camber 3.4% at 35.5% chord Source UIUC Airfoil Coordinates Database

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