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.

(n64012-il) NASA/LANGLEY 64-012 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(1)-012 airfoil Max thickness 12% at 40% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(n64012a-il) NACA 64-012A AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(1)-012A airfoil Max thickness 12% at 40% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(n64212-il) NACA 64(1)-212		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(1)-212 airfoil Max thickness 12% at 40% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(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

Page 78 of 164     68 69 70 71 72 73 74 75 76 77 78 79 80 81 82 83 84 85 86 87     Next

Please see the source web site or designer for any license conditions.