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.

(usa33-il) USA 33 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-33 airfoil Max thickness 14.2% at 29.9% chord Max camber 4.9% at 29.9% chord Max Cl/Cd 93.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe176-il) GOE 176 (ALBATROS 7020) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 176 (Albatros 7020) airfoil Max thickness 10.3% at 19.8% chord Max camber 5.6% at 39.8% chord Max Cl/Cd 93.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e331-il) EPPLER 331 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E331 flying wing airfoil Max thickness 11.2% at 28.3% chord Max camber 2.7% at 23.6% chord Max Cl/Cd 93.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(df102-il) DF102		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	David Fraser DF 102 low Reynolds number airfoil Max thickness 11% at 29.1% chord Max camber 2.4% at 43.5% chord Max Cl/Cd 93.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(s2046-il) S2046		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S2046 low Reynolds number airfoil Max thickness 9% at 26.2% chord Max camber 2.6% at 55.1% chord Max Cl/Cd 93.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(goe627-il) GOE 627 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 627 airfoil Max thickness 15.8% at 30% chord Max camber 4.1% at 30% chord Max Cl/Cd 93.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(s819-nr) NREL's S819 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S819 primary 21.0% Dia=10 to 20 m Re=1.0E+6 Clmax(S)=1.20 Clmax(R)=1.16 Restrained max lift coef Max thickness 21.1% at 28.4% chord Max camber 1.3% at 77.3% chord Max Cl/Cd 93.4 at Re# 1,000,000 Source NWTC National WInd Technology Center
(s3016-il) S3016-095-87		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S3016 low Reynolds number airfoil Max thickness 9.5% at 28.9% chord Max camber 1.8% at 43.1% chord Max Cl/Cd 93.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(mh20-il) MH 20 9.01%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 20 for F3D Pylon Racing Max thickness 9% at 32.2% chord Max camber 1.9% at 37.3% chord Max Cl/Cd 93.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca4421-il) NACA 4421		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 4421 airfoil Max thickness 21% at 30% chord Max camber 4% at 40% chord Max Cl/Cd 93.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database