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.

(goe693-il) GOE 693 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 693 airfoil Max thickness 12% at 30% chord Max camber 3.6% at 40% chord Max Cl/Cd 78.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe240-il) GOE 240 (KOLLER) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 240 (KOLLER) airfoil Max thickness 7% at 29.9% chord Max camber 5.2% at 39.9% chord Max Cl/Cd 78.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(hq2511-il) HQ 2.5/11 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 2.5/11 R/C sailplane airfoil Max thickness 11% at 33.9% chord Max camber 2.5% at 50% chord Max Cl/Cd 78.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(naca4412-il) NACA 4412		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 4412 airfoil Max thickness 12% at 30% chord Max camber 4% at 40% chord Max Cl/Cd 78.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s9037-il) S9037 (9%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S9037 (9%) low Reynolds number airfoil used on the Opus R/C sailplane Max thickness 9% at 28.5% chord Max camber 3.3% at 42.4% chord Max Cl/Cd 78.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(naca632615-il) NACA 63(2)-615		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(2)-615 airfoil Max thickness 15% at 34.8% chord Max camber 3.3% at 50% chord Max Cl/Cd 78.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e678-il) EPPLER 678 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E678 sailplane airfoil Max thickness 15.1% at 39.8% chord Max camber 5.1% at 53.7% chord Max Cl/Cd 78.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fx76mp140-il) FX 76-MP-140		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 76-MP-140 airfoil Max thickness 14.1% at 33.9% chord Max camber 7.1% at 46.7% chord Max Cl/Cd 78.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ah21-7-il) AH21 7% version (Andrew Hollom)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Andrew Hollom AH 21 airfoil (7% version) Max thickness 9% at 34.9% chord Max camber 2.3% at 54.8% chord Max Cl/Cd 78.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe178-il) GOE 178 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 178 airfoil Max thickness 8.5% at 30% chord Max camber 4.4% at 30% chord Max Cl/Cd 78.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database