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.

(goe101-il) GOE 101 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 101 airfoil Max thickness 6.9% at 30% chord Max camber 4% at 30% chord Max Cl/Cd 114.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe134-il) GOE 134 (MVA H.12) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 134 (MVA H.12) airfoil Max thickness 9.5% at 30% chord Max camber 4% at 30% chord Max Cl/Cd 114.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(sg6040-il) SG6040		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig / Giguere SG6040 wind turbine airfoil Max thickness 16% at 35.3% chord Max camber 2.3% at 60.5% chord Max Cl/Cd 114.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(raf38-il) RAF 38 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-38 airfoil Max thickness 12.7% at 30% chord Max camber 2.5% at 40% chord Max Cl/Cd 114.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe590-il) GOE 590 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 590 airfoil Max thickness 5.7% at 30% chord Max camber 4% at 30% chord Max Cl/Cd 114.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(goe190-il) GOE 190 (MVA MK.18) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 190 (MVA MK.18) airfoil Max thickness 12.7% at 19.7% chord Max camber 5.9% at 49.7% chord Max Cl/Cd 114.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca663418-il) NACA 66(3)-418		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66(3)-418 airfoil Max thickness 18% at 44.9% chord Max camber 2.2% at 50% chord Max Cl/Cd 114.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe692-il) GOE 692 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 692 airfoil Max thickness 16.1% at 30% chord Max camber 5% at 40% chord Max Cl/Cd 114.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(usa28-il) USA 28 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-28 airfoil Max thickness 13.2% at 29.9% chord Max camber 3.8% at 49.9% chord Max Cl/Cd 114.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e550-il) EPPLER 550 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E550 general aviation airfoil Max thickness 18.2% at 34% chord Max camber 2.2% at 29.4% chord Max Cl/Cd 114.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database