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.

(naca63a210-il) NACA 63A210		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63A210 airfoil Max thickness 10% at 34.9% chord Max camber 1.3% at 50% chord Max Cl/Cd 44.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ui1720-il) UNIVERSITY OF ILLINOIS UI-1720 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	University of Illinois UI-1720 high lift airfoil Max thickness 13.8% at 19% chord Max camber 4.6% at 21.2% chord Max Cl/Cd 44.9 at Re# 200,000 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 Max Cl/Cd 44.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(naca663418-il) NACA 66(3)-418		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66(3)-418 airfoil Max thickness 18% at 44.9% chord Max camber 2.2% at 50% chord Max Cl/Cd 44.9 at Re# 200,000 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 Max Cl/Cd 44.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(rae104-il) RAE 104 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE 104 airfoil Max thickness 10% at 42% chord Max camber 0% at 0% chord Max Cl/Cd 44.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(jn153-il) JN-153 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Narramore JN153 airfoil Max thickness 17.6% at 28.2% chord Max camber 8.4% at 38.1% chord Max Cl/Cd 44.6 at Re# 200,000 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 Max Cl/Cd 44.6 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(sc20612-il) NASA SC(2)-0612 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0612 airfoil (NASA TP-2969) Max thickness 12% at 37% chord Max camber 1.9% at 81% chord Max Cl/Cd 44.6 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(n14-il) N-14		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	N-14 airfoil Max thickness 11.5% at 30% chord Max camber 0.1% at 20% chord Max Cl/Cd 44.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database