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.

(hq2512-il) HQ 2.5/12 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 2.5/12 R/C sailplane airfoil Max thickness 12% at 35% chord Max camber 2.5% at 50% chord Max Cl/Cd 108.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(s9000-il) S9000 (9%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S9000 (9%) low Reynolds number airfoil used on the Blackhawk R/C sailplane Max thickness 9% at 28.2% chord Max camber 2.1% at 44.8% chord Max Cl/Cd 108.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe199-il) GOE 199 (L.F.G. 5406) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 199 (L.F.G. 5406) airfoil Max thickness 7.3% at 30% chord Max camber 5.2% at 30% chord Max Cl/Cd 108.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe457-il) GOE 457 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 457 airfoil Max thickness 7.8% at 19.9% chord Max camber 4.2% at 39.9% chord Max Cl/Cd 108.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(raf48-il) RAF-48 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-48 airfoil Max thickness 15% at 30% chord Max camber 2.9% at 40% chord Max Cl/Cd 108.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(mh80-il) MH 80 12.72%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 80 for flying wings (hang glider) Max thickness 12.7% at 21.7% chord Max camber 2.8% at 21.7% chord Max Cl/Cd 108.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe389-il) GOE 389 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 389 airfoil Max thickness 10.3% at 29.8% chord Max camber 4% at 39.8% chord Max Cl/Cd 108.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(waspsm-il) WASP (smoothed)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Mike Fox WASP low Reynolds number airfoil Max thickness 9.4% at 27.1% chord Max camber 3% at 37.9% chord Max Cl/Cd 108.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca634221-il) NACA 63(4)-221		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(4)-221 airfoil Max thickness 21% at 34.9% chord Max camber 1.1% at 50% chord Max Cl/Cd 108 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe133-il) GOE 133 (MVA H.11) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 133 (MVA H.11) airfoil Max thickness 7.9% at 30% chord Max camber 4.3% at 30% chord Max Cl/Cd 108 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database