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.

(glennmartin2-il) Glenn Martin 2		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Glenn Martin 2 airfoil Max thickness 13.5% at 20% chord Max camber 6.1% at 30% chord Source UIUC Airfoil Coordinates Database
(fx76mp160-il) FX 76-MP-160		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 76-MP-160 airfoil Max thickness 16.1% at 33.9% chord Max camber 6.1% at 50% chord Source UIUC Airfoil Coordinates Database
(fx73cl1152-il) FX 73-CL1-152		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 73-CL1-152 airfoil Max thickness 15.2% at 22.2% chord Max camber 6.1% at 33.9% chord Source UIUC Airfoil Coordinates Database
(eiffel10-il) Eiffel 10 (Wright) - 1903 Wright Flyer airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eiffel 10 (Wright) - 1903 Wright Flyer airfoil Max thickness 2.7% at 0% chord Max camber 6.1% at 40% chord Source UIUC Airfoil Coordinates Database
(naca6412-il) NACA 6412		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 6412 airfoil Max thickness 12% at 30.1% chord Max camber 6% at 39.6% chord Source UIUC Airfoil Coordinates Database
(n6409-il) NACA6409 9%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 6409 Max thickness 9% at 29.3% chord Max camber 6% at 39.6% chord Source UIUC Airfoil Coordinates Database
(m21-il) NACA M21 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-21 airfoil Max thickness 12% at 30% chord Max camber 6% at 30% chord Source UIUC Airfoil Coordinates Database
(m19-il) NACA M19 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-19 airfoil Max thickness 6.2% at 30% chord Max camber 6% at 30% chord Source UIUC Airfoil Coordinates Database
(lnv109a-il) LNV109A		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Douglas/Liebeck LNV109A high lift airfoil Max thickness 13% at 23.5% chord Max camber 6% at 31.5% chord Source UIUC Airfoil Coordinates Database
(goe798-il) GOE 798 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 798 airfoil Max thickness 20% at 30% chord Max camber 6% at 40% chord Source UIUC Airfoil Coordinates Database

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