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.

(mh82-il) MH 82 13.31%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 82 for flying wings (hang glider) Max thickness 13.3% at 24.6% chord Max camber 3.9% at 24.6% chord Max Cl/Cd 53.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(isa960-il) I.S.A. 960		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	I.S.A. 960 airfoil Max thickness 9.5% at 30% chord Max camber 4.5% at 40% chord Max Cl/Cd 53.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(v13009-il) BOEING VERTOL V(1.95)3009-1.25 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol V(1.9)3006-1.25 rotorcraft airfoil Max thickness 9% at 30.1% chord Max camber 1.3% at 20.1% chord Max Cl/Cd 53.7 at Re# 200,000 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 53.6 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(naca4424-il) NACA 4424		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 4424 airfoil Max thickness 24% at 29.4% chord Max camber 4% at 40% chord Max Cl/Cd 53.6 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(rae2822-il) RAE 2822 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE 2822 transonic airfoil Max thickness 12.1% at 37.9% chord Max camber 1.3% at 75.7% chord Max Cl/Cd 53.6 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(rae69ck-il) RAE6-9CK AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE6-9CK transonic airfoil Max thickness 12.1% at 37.9% chord Max camber 1.3% at 75.7% chord Max Cl/Cd 53.6 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e168-il) E168 (12.45%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E168 low Reynolds number airfoil Max thickness 12.4% at 26.7% chord Max camber 0% at 0% chord Max Cl/Cd 53.6 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(vr12-il) BOEING-VERTOL VR-12 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol/Dadone VR-12 rotorcraft airfoil Max thickness 10.6% at 35% chord Max camber 2.3% at 20% chord Max Cl/Cd 53.6 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(b707e-il) BOEING 707 .99 SPAN AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing Commercial Airplane Company model 707 airfoils Max thickness 9% at 42% chord Max camber 1.8% at 34% chord Max Cl/Cd 53.6 at Re# 200,000 Source UIUC Airfoil Coordinates Database