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.

(s6062-il) S6062 8%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S6062 low Reynolds number airfoil Max thickness 7.9% at 29.4% chord Max camber 1.4% at 43.7% chord Max Cl/Cd 50.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(daytonwrightt1-il) Dayton-Wright T-1		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Dayton-Wright T-1 airfoil Max thickness 13.4% at 30% chord Max camber 4.4% at 40% chord Max Cl/Cd 50.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(m11-il) NACA M11 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-11 airfoil Max thickness 8.2% at 30% chord Max camber 1.9% at 30% chord Max Cl/Cd 50.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(ec863914-il) EPPLER EC 86(-3)-914 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler EC 86(-3)-914 airfoil Max thickness 14.3% at 35.5% chord Max camber 4.4% at 71.2% chord Max Cl/Cd 50.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(usa29-il) USA 29 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-29 airfoil Max thickness 13.2% at 29.7% chord Max camber 5.5% at 39.7% chord Max Cl/Cd 50.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(goe318-il) GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 318 (Hansa-Brandenburg VI.5) airfoil Max thickness 9.1% at 29.9% chord Max camber 4.3% at 29.9% chord Max Cl/Cd 50.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(m18-il) NACA M18 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-18 airfoil Max thickness 12% at 30% chord Max camber 4.1% at 30% chord Max Cl/Cd 50.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(dormoy-il) Dormoy		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Dormoy airfoil Max thickness 9% at 30% chord Max camber 2.9% at 40% chord Max Cl/Cd 50.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e585-il) EPPLER 585 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E585 sailplane airfoil Max thickness 14.6% at 37.6% chord Max camber 4.2% at 42.8% chord Max Cl/Cd 50.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(lds2-il) LDS-2 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	LDS-2 airfoil Max thickness 12% at 34.9% chord Max camber 2.2% at 45% chord Max Cl/Cd 50.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database