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.

(naca747a315-il) NACA 747A315		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 747A315 airfoil Max thickness 15% at 40.2% chord Max camber 2.5% at 35% chord Max Cl/Cd 46.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(mh27-il) MH 27 11.99%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 27 for F3D Pylon Racing (extended laminar flow) Max thickness 12% at 42.4% chord Max camber 1.4% at 42.4% chord Max Cl/Cd 46.4 at Re# 100,000 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 46.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe646-il) GOE 646 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 646 airfoil Max thickness 18.3% at 29% chord Max camber 4.5% at 49% chord Max Cl/Cd 46.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(usa35a-il) USA 35 A AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-35A airfoil Max thickness 18.2% at 29.4% chord Max camber 6.4% at 39.4% chord Max Cl/Cd 46.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(goe503-il) GOE 503 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 503 airfoil Max thickness 15.6% at 29.7% chord Max camber 7% at 39.7% chord Max Cl/Cd 46.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(ag03-il) AG03 (flat aft bottom)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG03 (flat aft bottom) airfoil Max thickness 6.2% at 25.7% chord Max camber 2% at 33.1% chord Max Cl/Cd 46.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe462-il) GOE 462 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 462 airfoil Max thickness 11% at 9.9% chord Max camber 13.4% at 29.9% chord Max Cl/Cd 46.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(usa35-il) USA 35 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-35 airfoil Max thickness 18.2% at 29.4% chord Max camber 6.4% at 39.4% chord Max Cl/Cd 46.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca64210-il) NACA 64-210		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64-210 airfoil Max thickness 10% at 40% chord Max camber 1.1% at 50% chord Max Cl/Cd 46.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database