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.

(s4083-il) S4083 (8%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S4083 low Reynolds number airfoil Max thickness 8% at 22.5% chord Max camber 3.4% at 35.5% chord Max Cl/Cd 115.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe438-il) GOE 438 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 438 airfoil Max thickness 11% at 29.8% chord Max camber 3.8% at 39.8% chord Max Cl/Cd 115.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca4418-il) NACA 4418		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 4418 airfoil Max thickness 18% at 30% chord Max camber 4% at 40% chord Max Cl/Cd 115.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe377-il) GOE 377 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 377 airfoil Max thickness 6.5% at 30% chord Max camber 3.9% at 40% chord Max Cl/Cd 115.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe474-il) GOE 474 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 474 airfoil Max thickness 7% at 30% chord Max camber 2.9% at 40% chord Max Cl/Cd 115.8 at Re# 1,000,000 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 115.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(waspsm-il) WASP (smoothed)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Mike Fox WASP low Reynolds number airfoil Max thickness 9.4% at 27.1% chord Max camber 3% at 37.9% chord Max Cl/Cd 115.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(daytonwright6-il) Dayton-Wright 6		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Dayton-Wright 6 airfoil Max thickness 13.6% at 30% chord Max camber 4.9% at 40% chord Max Cl/Cd 115.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe549-il) GOE 549 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 549 airfoil Max thickness 13.9% at 30% chord Max camber 4.7% at 40% chord Max Cl/Cd 115.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(nlf416-il) NASA/LANGLEY NLF(1)-0416 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley/Somers NLF(1)-0416 natural laminar flow airfoil Max thickness 15.9% at 30.4% chord Max camber 2.5% at 34.8% chord Max Cl/Cd 115.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database