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.

(n63215-il) NACA 63-215 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(2)-215 airfoil Max thickness 15% at 34.9% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(n63215b-il) NACA 63(2)-215 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(2)-215 MOD B airfoil Max thickness 15% at 30% chord Max camber 1.5% at 10% chord Source UIUC Airfoil Coordinates Database
(n63415-il) NACA 63-415 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(2)-415 airfoil Max thickness 15% at 34.9% chord Max camber 2.2% at 50% chord Source UIUC Airfoil Coordinates Database
(n64015-il) NACA 642-015 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(2)-015 airfoil Max thickness 15% at 35% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(n64015a-il) NACA 642-015A AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(2)-015A airfoil Max thickness 15% at 40% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(n64215-il) NACA 64-215 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(2)-215 airfoil Max thickness 15% at 34.9% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca0015-il) NACA 0015		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0015 airfoil Max thickness 15% at 30% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(naca16015-il) NACA 16-015		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 16-015 airfoil Max thickness 15% at 50% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(naca23015-il) NACA 23015		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 23015 airfoil Max thickness 15% at 30% chord Max camber 1.8% at 15% chord Source UIUC Airfoil Coordinates Database
(naca2415-il) NACA 2415		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 2415 airfoil Max thickness 15% at 30% chord Max camber 2% at 40% chord Source UIUC Airfoil Coordinates Database

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