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.

(goe628-il) GOE 628 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 628 airfoil Max thickness 16.7% at 19.4% chord Max camber 5.6% at 39.3% chord Max Cl/Cd 84.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe391-il) GOE 391 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 391 airfoil Max thickness 5.1% at 40% chord Max camber 3.2% at 40% chord Max Cl/Cd 84.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(daytonwrightt1-il) Dayton-Wright T-1		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Dayton-Wright T-1 airfoil Max thickness 13.4% at 30% chord Max camber 4.4% at 40% chord Max Cl/Cd 84.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(s827-nr) NREL's S827 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S827 primary 21.0% Dia=40 to 50 m Re=4.0E+6 Clmax(S)=1.00 Clmax(R)=0.99 Restrained max lift coef Max thickness 21% at 44.9% chord Max camber 2.2% at 68% chord Max Cl/Cd 84.4 at Re# 500,000 Source NWTC National WInd Technology Center
(fx63147-il) FX 63-147 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 63-147 airfoil Max thickness 14.7% at 33.9% chord Max camber 3.1% at 33.9% chord Max Cl/Cd 84.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(n24-il) N-24		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	N-24 airfoil Max thickness 17% at 30% chord Max camber 5.4% at 40% chord Max Cl/Cd 84.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(oaf117-il) OAF117 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	ONERA/Aerospatiale OAF117 Fenestron airfoil Max thickness 11.5% at 23.2% chord Max camber 2% at 46.9% chord Max Cl/Cd 84.4 at Re# 500,000 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 84.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(clarym15-il) CLARK YM-15 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CLARK YM15 airfoil Max thickness 15% at 29.6% chord Max camber 3.6% at 39.6% chord Max Cl/Cd 84.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe645-il) GOE 645 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 645 airfoil Max thickness 15.4% at 19.4% chord Max camber 4.8% at 39.4% chord Max Cl/Cd 84.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database