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.

(goe515-il) GOE 515 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 515 airfoil Max thickness 8.5% at 30% chord Max camber 2.8% at 40% chord Source UIUC Airfoil Coordinates Database
(nacacyh-il) NACA CYH		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA CYH airfoil Max thickness 11.7% at 30% chord Max camber 2.8% at 40% chord Source UIUC Airfoil Coordinates Database
(e178-il) E178 (8.69%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E178 low Reynolds number airfoil Max thickness 8.7% at 29.8% chord Max camber 2.8% at 38.8% chord Source UIUC Airfoil Coordinates Database
(goe673-il) GOE 673 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 673 airfoil Max thickness 10.8% at 29.7% chord Max camber 2.8% at 49.7% chord Source UIUC Airfoil Coordinates Database
(e852-il) EPPLER E852 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E852 propeller airfoil Max thickness 10.1% at 37.2% chord Max camber 2.8% at 61.2% chord Source UIUC Airfoil Coordinates Database
(goe565-il) GOE 565 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 565 airfoil Max thickness 8.4% at 30% chord Max camber 2.8% at 50% chord Source UIUC Airfoil Coordinates Database
(s817-nr) NREL's S817 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S817 tip 16.0% Dia=30 to 50 m Re=3.0E+6 Clmax(S)=1.10 Clmax(R)=1.08 Restrained max lift coef Max thickness 16% at 51.1% chord Max camber 2.8% at 41.1% chord Source NWTC National WInd Technology Center
(sc21010-il) NASA SC(2)-1010 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-1010 airfoil Max thickness 10% at 32% chord Max camber 2.8% at 71% chord Source UIUC Airfoil Coordinates Database
(e818-il) EPPLER 818 HYDROFOIL AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E818 hydrofoil Max thickness 9.4% at 33.1% chord Max camber 2.8% at 67% chord Source UIUC Airfoil Coordinates Database
(e715-il) EPPLER 715 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E715 tailplane airfoil Max thickness 15% at 33.1% chord Max camber 2.8% at 42% chord Source UIUC Airfoil Coordinates Database

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