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.

(naca634421-il) NACA 63(4)-421		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(4)-421 airfoil Max thickness 21% at 34.8% chord Max camber 2.2% at 50% chord Max Cl/Cd 109.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e642-il) EPPLER 642 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E642 sailplane airfoil Max thickness 15.1% at 39.4% chord Max camber 3% at 39.4% chord Max Cl/Cd 109.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(s4053-il) S4053		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S4053 low Reynolds number airfoil Max thickness 8.9% at 30.9% chord Max camber 3% at 45% chord Max Cl/Cd 109.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(usa35a-il) USA 35 A AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-35A airfoil Max thickness 18.2% at 29.4% chord Max camber 6.4% at 39.4% chord Max Cl/Cd 109.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(fx83w160-il) FX 83-W-160		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 83-W-160 airfoil for use on wind turbines (W) Max thickness 16.1% at 37.1% chord Max camber 3.9% at 62.9% chord Max Cl/Cd 109.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(s827-nr) NREL's S827 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S827 primary 21.0% Dia=40 to 50 m Re=4.0E+6 Clmax(S)=1.00 Clmax(R)=0.99 Restrained max lift coef Max thickness 21% at 44.9% chord Max camber 2.2% at 68% chord Max Cl/Cd 109.6 at Re# 1,000,000 Source NWTC National WInd Technology Center
(a18-il) A18 (original)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Archer A18 F1C free flight airfoil(original) Max thickness 7.3% at 30% chord Max camber 3.9% at 45% chord Max Cl/Cd 109.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(hq358-il) HQ 3.5/8 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 3.5/8 R/C sailplane airfoil Max thickness 8% at 35% chord Max camber 3.5% at 50% chord Max Cl/Cd 109.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe650-il) GOE 650 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 650 airfoil Max thickness 13.4% at 19.5% chord Max camber 4.4% at 49.5% chord Max Cl/Cd 109.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe382-il) GOE 382 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 382 airfoil Max thickness 20% at 29% chord Max camber 6% at 39% chord Max Cl/Cd 109.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database