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.

(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 91 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe617-il) GOE 617 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 617 airfoil Max thickness 13.9% at 30% chord Max camber 2.2% at 30% chord Max Cl/Cd 91 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe505-il) GOE 505 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 505 airfoil Max thickness 14% at 19.7% chord Max camber 5.9% at 39.7% chord Max Cl/Cd 91 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca23015-il) NACA 23015		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 23015 airfoil Max thickness 15% at 30% chord Max camber 1.8% at 15% chord Max Cl/Cd 91 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(s811-nr) NREL's S811 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S811 root Max thickness 26.3% at 27.4% chord Max camber 1.7% at 76.4% chord Max Cl/Cd 90.9 at Re# 1,000,000 Source NWTC National WInd Technology Center

(ag19-il) AG19		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG19 airfoil Max thickness 5.4% at 20.6% chord Max camber 2.2% at 44.2% chord Max Cl/Cd 90.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(s1046-il) S1046 17% (Danny Howell)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S1046 airfoil Max thickness 17% at 30.8% chord Max camber 0% at 0% chord Max Cl/Cd 90.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(p51htip-il) NACA 66		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66 Max thickness 12% at 45% chord Max camber 1.3% at 47.5% chord Max Cl/Cd 90.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e472-il) EPPLER 472 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E472 aerobatic aircraft airfoil Max thickness 12.1% at 17.5% chord Max camber 0% at 0% chord Max Cl/Cd 90.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(mh64-il) MH 64 8.59%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 64 for flying wings Max thickness 8.6% at 26.9% chord Max camber 1.4% at 41.8% chord Max Cl/Cd 90.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database