Airfoil Tools
Search 1638 airfoils

You have 0 airfoils loaded.
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.

(2032c-il) 20-32C AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Dillner 20-32-C low Reynolds number airfoil Max thickness 8% at 20% chord Max camber 6.9% at 40% chord Max Cl/Cd 54.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe300-il) GOE 300 (FRIEDRICHSHAFEN G20) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 300 (Friedrichshafen G20) airfoil Max thickness 8.4% at 30% chord Max camber 6.7% at 30% chord Max Cl/Cd 54.9 at Re# 100,000 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 54.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe529-il) GOE 529 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 529 airfoil Max thickness 9.7% at 29.9% chord Max camber 5.8% at 39.9% chord Max Cl/Cd 54.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(n63412-il) NACA 63-412 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(1)-412 airfoil Max thickness 12% at 34.9% chord Max camber 2.2% at 50% chord Max Cl/Cd 54.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(fx84w127-il) FX 84-W-127		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 84-W-127 airfoil for use on wind turbines (W) Max thickness 12.8% at 33.9% chord Max camber 3.7% at 40.2% chord Max Cl/Cd 54.8 at Re# 100,000 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 54.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe533-il) GOE 533 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 533 airfoil Max thickness 13.7% at 30% chord Max camber 4.7% at 40% chord Max Cl/Cd 54.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe701-il) GOE 701 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 701 airfoil Max thickness 12.5% at 29.6% chord Max camber 4.9% at 39.6% chord Max Cl/Cd 54.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(s2091-il) S2091-101-83		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S2091 low Reynolds number airfoil Max thickness 10.1% at 26% chord Max camber 3.7% at 39.5% chord Max Cl/Cd 54.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database