Airfoil Tools
Search 1638 airfoils

You have 0 airfoils loaded.
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.

(goe393-il) GOE 393 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 393 airfoil Max thickness 6.1% at 19.9% chord Max camber 4.2% at 29.9% chord Max Cl/Cd 57.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe591-il) GOE 591 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 591 airfoil Max thickness 11.2% at 30% chord Max camber 5.1% at 40% chord Max Cl/Cd 57.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e591-il) E591		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E591 airfoil Max thickness 15.7% at 25% chord Max camber 6% at 52.3% chord Max Cl/Cd 57.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(dae31-il) DAE-31 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela DAE31 low Reynolds number airfoil Max thickness 11.1% at 29.3% chord Max camber 6.7% at 47% chord Max Cl/Cd 57.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe492-il) GOE 492 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 492 airfoil Max thickness 6.2% at 29.9% chord Max camber 3.4% at 49.9% chord Max Cl/Cd 57.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(fg1-il) Fage & Collins 1		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Fage & Collins 1 airfoil Max thickness 8.2% at 30% chord Max camber 3.1% at 40% chord Max Cl/Cd 57.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe188-il) GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 188 (Schatte-Lanz 3U10) airfoil Max thickness 8.9% at 30% chord Max camber 4.3% at 30% chord Max Cl/Cd 57.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(s4158-il) S4158		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S4158 low Reynolds number airfoil Max thickness 10.9% at 35.3% chord Max camber 3.7% at 44.7% chord Max Cl/Cd 57.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe442-il) GOE 442 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 442 airfoil Max thickness 7.7% at 19.9% chord Max camber 4.3% at 39.9% chord Max Cl/Cd 57.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(sg6051-il) SG6051		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig / Giguere SG6051 wind turbine airfoil Max thickness 12% at 35.7% chord Max camber 3.1% at 49.9% chord Max Cl/Cd 57.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database