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.

(ag14-il) AG14		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG14 airfoil Max thickness 5.4% at 19.9% chord Max camber 2% at 41.9% chord Max Cl/Cd 62.2 at Re# 200,000 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 Max Cl/Cd 62.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(raf26-il) RAF 26 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-26 airfoil Max thickness 6.6% at 29.9% chord Max camber 2.1% at 49.9% chord Max Cl/Cd 62.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ag13-il) AG13		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG13 airfoil Max thickness 5.8% at 21.3% chord Max camber 2% at 41.8% chord Max Cl/Cd 62.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(kc135a-il) KC-135 BL52.44 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing KC-135 transonic airfoils Max thickness 15.5% at 35% chord Max camber 1.3% at 20% chord Max Cl/Cd 62.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(du84132v-il) DELFT DU84-132V3 AIRFOIL (MEASURED)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Airfoil measured from an ASW22 wing Max thickness 13.6% at 33.9% chord Max camber 3.1% at 45.3% chord Max Cl/Cd 62.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e339-il) EPPLER 339 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E339 flying wing airfoil Max thickness 13.5% at 30.1% chord Max camber 4.1% at 25.2% chord Max Cl/Cd 62.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(m8-il) NACA M8 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-8 airfoil Max thickness 11.7% at 15% chord Max camber 8% at 30% chord Max Cl/Cd 62.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(usa45-il) USA 45 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-45 airfoil Max thickness 14.5% at 29.8% chord Max camber 4.1% at 29.8% chord Max Cl/Cd 62 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ls413mod-il) NASA/LANGLEY LS(1)-0413MOD AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley LS(1)-0413MOD general aviation airfoil Max thickness 13% at 35% chord Max camber 2.2% at 40% chord Max Cl/Cd 62 at Re# 200,000 Source UIUC Airfoil Coordinates Database