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.

(ag03-il) AG03 (flat aft bottom)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG03 (flat aft bottom) airfoil Max thickness 6.2% at 25.7% chord Max camber 2% at 33.1% chord Max Cl/Cd 34.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ag44ct02r-il) AG44ct -02f		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG44ct -02f airfoil Max thickness 7.3% at 24.6% chord Max camber 1.9% at 34.4% chord Max Cl/Cd 34.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe491-il) GOE 491 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 491 airfoil Max thickness 4.9% at 20% chord Max camber 2.9% at 30% chord Max Cl/Cd 34.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe285-il) GOE 285 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 285 airfoil Max thickness 11.7% at 30% chord Max camber 3.7% at 30% chord Max Cl/Cd 34.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(c141f-il) LOCKHEED C-141 BL958.89 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-141 transonic wing airfoils Max thickness 10% at 40.2% chord Max camber 2.3% at 45.1% chord Max Cl/Cd 34.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(ag11-il) AG11		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG11 airfoil Max thickness 5.8% at 26% chord Max camber 2.2% at 29.7% chord Max Cl/Cd 34.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(s2050-il) S2050 8.93%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S2050 low Reynolds number airfoil Max thickness 8.9% at 29.8% chord Max camber 1.1% at 69.5% chord Max Cl/Cd 34.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(s826-nr) NREL's S826 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S826 tip 14.0% Dia=20 to 40 m Re=1.5E+6 Clmax(S)=1.42 Clmax(R)=1.31 High max lift coef Max thickness 14% at 33.7% chord Max camber 4.3% at 62% chord Max Cl/Cd 34.6 at Re# 50,000 Source NWTC National WInd Technology Center
(rg15a213-il) RG 15A 2.5/13.0 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rolf Girsberger RG 15A 2.5/13.0 airfoil Max thickness 13% at 30.2% chord Max camber 2.5% at 39.7% chord Max Cl/Cd 34.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(s6062-il) S6062 8%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S6062 low Reynolds number airfoil Max thickness 7.9% at 29.4% chord Max camber 1.4% at 43.7% chord Max Cl/Cd 34.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database