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.

(goe780-il) GOE 780 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 780 airfoil Max thickness 12% at 50% chord Max camber 1% at 40% chord Max Cl/Cd 12.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca654221-il) NACA 65(4)-221		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65(4)-221 airfoil Max thickness 21% at 39.9% chord Max camber 1.1% at 50% chord Max Cl/Cd 12.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fx66a175-il) WORTMANN FX 66-17A-175 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 66-17A-175 airfoil Max thickness 17.5% at 33.9% chord Max camber 4.2% at 40.2% chord Max Cl/Cd 12.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe505-il) GOE 505 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 505 airfoil Max thickness 14% at 19.7% chord Max camber 5.9% at 39.7% chord Max Cl/Cd 12.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(clarym15-il) CLARK YM-15 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CLARK YM15 airfoil Max thickness 15% at 29.6% chord Max camber 3.6% at 39.6% chord Max Cl/Cd 12.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(mh80-il) MH 80 12.72%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 80 for flying wings (hang glider) Max thickness 12.7% at 21.7% chord Max camber 2.8% at 21.7% chord Max Cl/Cd 12.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca644221-il) NACA 64(4)-221		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(4)-221 airfoil Max thickness 21% at 34.9% chord Max camber 1.1% at 50% chord Max Cl/Cd 12.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca664221-il) NACA 66(4)-221		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66(4)-221 airfoil Max thickness 21% at 45% chord Max camber 1.1% at 50% chord Max Cl/Cd 12.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ua79sfm-il) UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL MAIN ELEMENT		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	University of Alberta/Marsden UA 79-SF-187 sailplane airfoil MAIN ELEMENT Max thickness 18.8% at 42.8% chord Max camber 3% at 66.9% chord Max Cl/Cd 12.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(r1082-il) RONCZ 1082 VOYAGER ROOT OUTER AFT WING AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Roncz 1082 Voyager root outer aft wing airfoil Max thickness 18% at 40% chord Max camber 3.4% at 40% chord Max Cl/Cd 12.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database