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.

(rg14-il) RG 14 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rolf Girsberger RG 14 airfoil Max thickness 8.5% at 29.7% chord Max camber 1.6% at 39.2% chord Max Cl/Cd 83.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(fx66h80-il) FX 66-H-80		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 66-H-80 airfoil Max thickness 8% at 27.9% chord Max camber 2.5% at 25% chord Max Cl/Cd 83.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(s818-nr) NREL's S818 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S818 root 24.0% Dia=30 to 50 m Re=2.5E+6 Clmax(S)=1.68 Clmax(R)=1.61 Restrained max lift coef Max thickness 24% at 30.9% chord Max camber 3.3% at 74.2% chord Max Cl/Cd 83.4 at Re# 500,000 Source NWTC National WInd Technology Center
(naca2418-il) NACA 2418		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 2418 airfoil Max thickness 18% at 30% chord Max camber 2% at 40% chord Max Cl/Cd 83.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(hq208-il) HQ 2.0/8 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 2.0/8 R/C sailplane airfoil Max thickness 8% at 35% chord Max camber 2% at 50% chord Max Cl/Cd 83.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(rg8-il) RG 8 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rolf Girsberger RG 8 airfoil Max thickness 10.8% at 31.1% chord Max camber 2.2% at 60.5% chord Max Cl/Cd 83.3 at Re# 500,000 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 83.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(raf19-il) RAF 19 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-19 airfoil Max thickness 10.5% at 15% chord Max camber 10.1% at 40% chord Max Cl/Cd 83.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(s810-nr) NREL's S810 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S810 tip Max thickness 18% at 44.2% chord Max camber 0.9% at 10.9% chord Max Cl/Cd 83.2 at Re# 500,000 Source NWTC National WInd Technology Center
(goe434-il) GOE 434 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 434 airfoil Max thickness 22.8% at 28.4% chord Max camber 5.2% at 48.5% chord Max Cl/Cd 83.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database