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.

(e654-il) EPPLER 654 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E654 sailplane airfoil Max thickness 17.2% at 36.1% chord Max camber 4.9% at 46.5% chord Max Cl/Cd 32.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(s9032-il) S9032 (9%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S9032 (9%) symmetrical horizontal stab airfoil used on the Blackhawk R/C sailplane Max thickness 9% at 25% chord Max camber 0% at 0% chord Max Cl/Cd 32.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca662415-il) NACA 66(2)-415		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66(2)-415 airfoil Max thickness 15% at 45% chord Max camber 2.2% at 50% chord Max Cl/Cd 32.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(du06-w-200-dt) DU 06-W-200 VAWT airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	DU 06-W-200 airfoil for Small Vertical Axis Wind Turbines (VAWT) Max thickness 19.8% at 31.1% chord Max camber 0.5% at 84.6% chord Max Cl/Cd 32.7 at Re# 100,000 Source TU Delft
(naca661212-il) NACA 66(1)-212		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66(1)-212 airfoil Max thickness 12% at 45% chord Max camber 1.1% at 50% chord Max Cl/Cd 32.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(goe420-il) GOE 420 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 420 airfoil Max thickness 18.8% at 30% chord Max camber 4.3% at 50% chord Max Cl/Cd 32.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(esa40-il) ESA40		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Evans Simitar Airfoil ESA40 for R/C tailless aircraft Max thickness 10.7% at 27.1% chord Max camber 2% at 12% chord Max Cl/Cd 32.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e230-il) E230 (9.96%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E230 airfoil Max thickness 10% at 29.3% chord Max camber 0% at 0% chord Max Cl/Cd 32.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(dae11-il) DAE-11 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela DAE11 low Reynolds number airfoil Max thickness 12.8% at 32.8% chord Max camber 6.6% at 44.4% chord Max Cl/Cd 32.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e583-il) EPPLER 583 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E583 sailplane airfoil Max thickness 16.5% at 38% chord Max camber 4.5% at 38% chord Max Cl/Cd 32.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database