Airfoil Tools
Search 1638 airfoils

You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

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.

(naca23021-il) NACA 23021		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 23021 airfoil Max thickness 21% at 30% chord Max camber 1.9% at 10% chord Source UIUC Airfoil Coordinates Database
(naca23024-il) NACA 23024		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 23024 airfoil Max thickness 24% at 30.3% chord Max camber 2.9% at 1.3% 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
(naca2408-il) NACA 2408		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 2408 airfoil Max thickness 8% at 29.9% chord Max camber 2% at 40% chord Source UIUC Airfoil Coordinates Database
(naca2410-il) NACA 2410		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 2410 airfoil Max thickness 10% at 29.9% chord Max camber 2% at 40% chord Source UIUC Airfoil Coordinates Database

(naca24112-jf) NACA 24112		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file
	NACA 24112 5 digit reflex airfoil Max thickness 12% at 29.4% chord Max camber 1.7% at 20.6% chord Source Javafoil generated
(naca2412-il) NACA 2412		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 2412 airfoil Max thickness 12% at 30% chord Max camber 2% at 40% chord Source UIUC Airfoil Coordinates Database
(n2414-il) NACA 2414		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 2414 airfoil Max thickness 14% at 29.5% chord Max camber 2% at 39.6% 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
(n2415-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 29.5% chord Max camber 2% at 39.6% chord Source UIUC Airfoil Coordinates Database