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.

(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 128.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca653618-il) NACA 65(3)-618		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65(3)-618 airfoil Max thickness 18% at 39.8% chord Max camber 3.3% at 50% chord Max Cl/Cd 128.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe744-il) GOE 744 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 744 airfoil Max thickness 14.5% at 20% chord Max camber 7% at 30% chord Max Cl/Cd 128.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e598-il) EPPLER 598 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E598 airfoil Max thickness 11.1% at 24.2% chord Max camber 4.5% at 34.4% chord Max Cl/Cd 128.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e205-il) E205 (10.48%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E205 low Reynolds number airfoil Max thickness 10.5% at 29.7% chord Max camber 2.5% at 38.7% chord Max Cl/Cd 128.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(goe301-il) GOE 301 (FRIEDRICHSHAFEN G 13) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 301 (Friedrichshafen G 13) airfoil Max thickness 10% at 28.9% chord Max camber 6.5% at 39.9% chord Max Cl/Cd 128.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e561-il) EPPLER 561 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E561 general aviation airfoil Max thickness 16.9% at 27.9% chord Max camber 5.1% at 45.8% chord Max Cl/Cd 128.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca654421a05-il) NACA 65(4)-421 a=0.5		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65(4)-421 a=0.5 airfoil Max thickness 21% at 39.9% chord Max camber 3% at 45% chord Max Cl/Cd 128.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(s2091-il) S2091-101-83		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S2091 low Reynolds number airfoil Max thickness 10.1% at 26% chord Max camber 3.7% at 39.5% chord Max Cl/Cd 128.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e582-il) EPPLER 582 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E582 sailplane airfoil Max thickness 14.7% at 37.8% chord Max camber 4.2% at 43.1% chord Max Cl/Cd 128.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database