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.

(s6061-il) S6061 9%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S6061 low Reynolds number airfoil Max thickness 9% at 34% chord Max camber 1.5% at 43.6% chord Source UIUC Airfoil Coordinates Database
(s7075-il) S7075 (9%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S7075 low Reynolds number airfoil Max thickness 9% at 29% chord Max camber 2.8% at 46.8% chord 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 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
(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

(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
(sd2083-il) SD2083 (9.0%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD2083 low Reynolds number airfoil Max thickness 9% at 35.2% chord Max camber 2.5% at 49.6% chord Source UIUC Airfoil Coordinates Database
(ssca09-il) SIKORSKY SSC-A09 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Sikorsky/Flemming SSC-A09 transonic rotorcraft airfoil Max thickness 9% at 37.7% chord Max camber 1.2% at 17.2% chord Source UIUC Airfoil Coordinates Database
(v13009-il) BOEING VERTOL V(1.95)3009-1.25 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol V(1.9)3006-1.25 rotorcraft airfoil Max thickness 9% at 30.1% chord Max camber 1.3% at 20.1% chord Source UIUC Airfoil Coordinates Database
(ys900-il) YS-900		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	YS900 hyrdofoil (Shen / Eppler) Max thickness 9% at 52.5% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database