Airfoil Tools
Search 1638 airfoils

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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.

(s835-nr) NREL's S835 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S835 root 21.0% Dia=1 to 3 m Re=2.5E+5 Clmax(S)=1.20 Clmax(R)=1.03 High max lift coef Max thickness 21% at 30.5% chord Max camber 2.4% at 78% chord Source NWTC National WInd Technology Center
(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 Source UIUC Airfoil Coordinates Database
(s9026-il) S9026 (9.5%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S9026 (9.5%) symmetrical horizontal stab airfoil used on the Opus R/C sailplane Max thickness 9.5% at 27.3% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(s9027-il) S9027 (8%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S9027 (8%) symmetrical vertical stab airfoil used on the Opus R/C sailplane Max thickness 8% at 22.9% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(s9032-il) S9032 (9%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S9032 (9%) symmetrical horizontal stab airfoil used on the Blackhawk R/C sailplane Max thickness 9% at 25% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database

(s9033-il) S9033 (7.5%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S9033 (7.5%) symmetrical vertical stab airfoil used on the Blackhawk R/C sailplane Max thickness 7.5% at 22.8% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(s9037-il) S9037 (9%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S9037 (9%) low Reynolds number airfoil used on the Opus R/C sailplane Max thickness 9% at 28.5% chord Max camber 3.3% at 42.4% chord Source UIUC Airfoil Coordinates Database
(sa7024-il) SA7024		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig / Ashok Gopalarathnam SA7024 low Reynolds number airfoil Max thickness 7% at 25.9% chord Max camber 3.3% at 43.3% chord Source UIUC Airfoil Coordinates Database
(sa7025-il) SA7025		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig / Ashok Gopalarathnam SA7025 low Reynolds number airfoil Max thickness 8% at 29.2% chord Max camber 3.6% at 43.2% chord Source UIUC Airfoil Coordinates Database
(sa7026-il) SA7026		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig / Ashok Gopalarathnam SA7026 low Reynolds number airfoil Max thickness 9% at 32.9% chord Max camber 3.8% at 47.1% chord Source UIUC Airfoil Coordinates Database