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.

(goe256-il) GOE 256 (JUNKERS E) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 256 (JUNKERS E) airfoil Max thickness 16% at 29.6% chord Max camber 4.7% at 39.6% chord Max Cl/Cd 86.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(s8055-il) S8055 (12%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S8055 (12%) low Reynolds number airfoil Max thickness 12% at 33.9% chord Max camber 1.6% at 44.7% chord Max Cl/Cd 86.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(amsoil1-il) RUTAN CANARD AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rutan AMSOIL racer canard airfoil Max thickness 11.6% at 39% chord Max camber 2.1% at 42% chord Max Cl/Cd 86.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(naca654221-il) NACA 65(4)-221		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65(4)-221 airfoil Max thickness 21% at 39.9% chord Max camber 1.1% at 50% chord Max Cl/Cd 86.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(s823-nr) NREL's S823 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S823 root 21.0% Dia=2 to 10 m Re=4.0E+5 Clmax(S)=1.20 Clmax(R)=1.16 Restrained max lift coef Max thickness 21.2% at 24.3% chord Max camber 2.4% at 70.5% chord Max Cl/Cd 86.1 at Re# 500,000 Source NWTC National WInd Technology Center

(goe676-il) GOE 676 (= M 12) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 676 (= M 12) airfoil Max thickness 11.9% at 30% chord Max camber 2% at 30% chord Max Cl/Cd 86.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe770-il) GOE 770 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 770 airfoil Max thickness 21% at 30% chord Max camber 4% at 30% chord Max Cl/Cd 86.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(e332-il) EPPLER 332 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E332 flying wing airfoil Max thickness 11.5% at 32.3% chord Max camber 3.1% at 22.6% chord Max Cl/Cd 86 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe769-il) GOE 769 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 769 airfoil Max thickness 13.8% at 20% chord Max camber 4.8% at 30% chord Max Cl/Cd 85.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(naca25112-jf) NACA 25112		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file
	NACA 25112 5 digit reflex airfoil Max thickness 12% at 29.5% chord Max camber 2% at 27.2% chord Max Cl/Cd 85.9 at Re# 500,000 Source Javafoil generated