Airfoil Tools
Search 1638 airfoils

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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.

(naca654421-il) NACA 65(4)-421		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65(4)-421 airfoil Max thickness 21% at 39.9% chord Max camber 2.2% at 50% chord Source UIUC Airfoil Coordinates Database
(naca654421a05-il) NACA 65(4)-421 a=0.5		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65(4)-421 a=0.5 airfoil Max thickness 21% at 39.9% chord Max camber 3% at 45% chord Source UIUC Airfoil Coordinates Database
(naca65206-il) NACA 65-206		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65-206 airfoil Max thickness 6% at 40% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca65209-il) NACA 65-209		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65-209 airfoil Max thickness 9% at 40% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca65210-il) NACA 65-210		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65-210 airfoil Max thickness 10% at 40% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database

(naca65410-il) NACA 65-410		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65-410 airfoil Max thickness 10% at 39.9% chord Max camber 2.2% at 50% chord Source UIUC Airfoil Coordinates Database
(p51hroot-il) NACA 66		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66 Max thickness 15.5% at 45% chord Max camber 1.3% at 47.5% chord Source UIUC Airfoil Coordinates Database
(p51htip-il) NACA 66		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66 Max thickness 12% at 45% chord Max camber 1.3% at 47.5% chord Source UIUC Airfoil Coordinates Database
(naca661212-il) NACA 66(1)-212		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66(1)-212 airfoil Max thickness 12% at 45% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database
(naca662215-il) NACA 66(2)-215		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66(2)-215 airfoil Max thickness 15% at 45% chord Max camber 1.1% at 50% chord Source UIUC Airfoil Coordinates Database