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.

(n64212ma-il) NACA 64(1)-212 MOD A		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA-NASA/AMES/Hicks 63(1)-212 MOD A airfoil Max thickness 12% at 41.2% chord Max camber 2.5% at 21.5% chord Source UIUC Airfoil Coordinates Database
(n64212mb-il) NACA 64(1)-212 MOD B		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA-NASA/AMES/Hicks 63(1)-212 MOD B airfoil Max thickness 12% at 34.9% chord Max camber 1.5% at 9.9% chord Source UIUC Airfoil Coordinates Database
(n8h12-il) NACA 8-H-12 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 8-H-12 rotorcraft airfoil Max thickness 12% at 30% chord Max camber 3.5% at 30% chord Source UIUC Airfoil Coordinates Database
(naca001234-il) NACA 0012-34		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0012-34 airfoil Max thickness 12% at 40% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(naca001264-il) NACA 0012-64		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0012-64 airfoil Max thickness 12% at 40% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(naca1412-il) NACA 1412		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 1412 airfoil Max thickness 12% at 29.9% chord Max camber 1% at 40% chord Source UIUC Airfoil Coordinates Database
(naca16012-il) NACA 16-012		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 16-012 airfoil Max thickness 12% at 50% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(naca22112-jf) NACA 22112		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file
	NACA 22112 5 digit reflex airfoil Max thickness 12% at 29.5% chord Max camber 0.8% at 9.6% chord Source Javafoil generated
(naca23012-il) NACA 23012 12%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 23012 airfoil Max thickness 12% at 29.8% chord Max camber 1.8% at 12.7% chord Source UIUC Airfoil Coordinates Database
(naca23112-jf) NACA 23112		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file
	NACA 23112 5 digit reflex airfoil Max thickness 12% at 29.5% chord Max camber 1.2% at 14.7% chord Source Javafoil generated

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