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.

(n22-il) N-22		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	N-22 airfoil Max thickness 12.4% at 30% chord Max camber 4% at 40% chord Source UIUC Airfoil Coordinates Database
(naca4412-il) NACA 4412		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 4412 airfoil Max thickness 12% at 30% chord Max camber 4% at 40% chord Source UIUC Airfoil Coordinates Database
(naca4415-il) NACA 4415		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 4415 airfoil Max thickness 15% at 30.9% chord Max camber 4% at 40.2% chord Source UIUC Airfoil Coordinates Database
(naca4418-il) NACA 4418		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 4418 airfoil Max thickness 18% at 30% chord Max camber 4% at 40% chord Source UIUC Airfoil Coordinates Database
(naca4421-il) NACA 4421		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 4421 airfoil Max thickness 21% at 30% chord Max camber 4% at 40% chord Source UIUC Airfoil Coordinates Database
(naca4424-il) NACA 4424		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 4424 airfoil Max thickness 24% at 29.4% chord Max camber 4% at 40% chord Source UIUC Airfoil Coordinates Database
(nlf0215f-il) NASA/LANGLEY NLF(1)-0215F AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley/Somers NLF(1)-0215F natural laminar flow airfoil Max thickness 15% at 37.7% chord Max camber 4% at 42.3% chord Source UIUC Airfoil Coordinates Database
(psu94097-il) PSU 94-097 (AIAA 2001-2478)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Maughmer PSU 94-097 winglet airfoil Max thickness 9.7% at 32.3% chord Max camber 4% at 46.3% chord Source UIUC Airfoil Coordinates Database
(raf32md-il) RAF 32 MOD AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-32 MOD airfoil Max thickness 10.2% at 30% chord Max camber 4% at 50% chord Source UIUC Airfoil Coordinates Database
(s4062-il) S4062-095-87		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S4062 low Reynolds number airfoil Max thickness 9.5% at 31.7% chord Max camber 4% at 50.4% chord Source UIUC Airfoil Coordinates Database

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