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.

(n63210-il) NACA 63-210 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63-210 airfoil Max thickness 10% at 35% chord Max camber 1.1% at 60% chord Source UIUC Airfoil Coordinates Database
(n64110-il) NACA 64-110 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64-110 airfoil Max thickness 10% at 40% chord Max camber 0.6% at 50% chord Source UIUC Airfoil Coordinates Database
(n6h10-il) NACA 6-H-10 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 6-H-10 rotorcraft airfoil Max thickness 10% at 40% chord Max camber 4.6% at 40% chord Source UIUC Airfoil Coordinates Database
(naca0010-il) NACA 0010		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0010 airfoil Max thickness 10% at 30% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(naca001034-il) NACA 0010-34		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0010-34 airfoil Max thickness 10% at 40% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(naca001034a08cli02-il) NACA 0010-34 a=0.8 c(li)=0.2		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0010-34 a=0.8 c(li)=0.2 airfoil Max thickness 10% at 40% chord Max camber 1.3% at 50% chord Source UIUC Airfoil Coordinates Database
(naca001035-il) NACA 0010-35		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0010-35 airfoil Max thickness 10% at 50% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(naca001064-il) NACA 0010-64		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0010-64 airfoil Max thickness 10% at 40% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(naca001065-il) NACA 0010-65		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0010-65 airfoil Max thickness 10% at 50% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(naca001066-il) NACA 0010-66		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0010-66 airfoil Max thickness 10% at 60% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database

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