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.

(s810-nr) NREL's S810 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S810 tip Max thickness 18% at 44.2% chord Max camber 0.9% at 10.9% chord Source NWTC National WInd Technology Center
(ssca07-il) SIKORSKY SSC-A07 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Sikorsky/Flemming SSC-A07 transonic rotorcraft airfoil Max thickness 7% at 37.7% chord Max camber 0.9% at 17.2% chord Source UIUC Airfoil Coordinates Database
(supermarine371i-il) Supermarine 371-I (root)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Supermarine 371-I root airfoil Max thickness 13% at 40% chord Max camber 0.9% at 50% chord Source UIUC Airfoil Coordinates Database
(supermarine371ii-il) Supermarine 371-II (tip)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Supermarine 371-II tip airfoil Max thickness 8.4% at 50% chord Max camber 0.9% at 45% chord Source UIUC Airfoil Coordinates Database
(tempest2-il) HAWKER TEMPEST 61% SEMISPAN AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Hawker Tempest 61% semispan airfoil (NPL?) Max thickness 12% at 37.3% chord Max camber 0.9% at 39.3% chord Source UIUC Airfoil Coordinates Database

(v13006-il) BOEING VERTOL V13006-.7 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol V13006-.7 rotorcraft airfoil Max thickness 6% at 30.2% chord Max camber 0.9% at 20.2% chord Source UIUC Airfoil Coordinates Database
(amsoil2-il) RUTAN WING AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rutan AMSOIL racer wing airfoil Max thickness 11.8% at 39% chord Max camber 1% at 48% chord Source UIUC Airfoil Coordinates Database
(as5045-il) AS5045 (15%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	AS5045 airfoil Ashok Gopalarathnam/Selig 15% airfoil Max thickness 15% at 37.5% chord Max camber 1% at 27.2% chord Source UIUC Airfoil Coordinates Database
(du8608418-il) DU86-084/18 8.44%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Deflt University DU 86-084/18 low Reynolds number airfoil Max thickness 8.5% at 36.9% chord Max camber 1% at 45.8% chord Source UIUC Airfoil Coordinates Database
(eh1070-il) Eh 1.0/7.0		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	John Yost EH 1.0/7.0 for tailless R/C aircraft Max thickness 7% at 28.7% chord Max camber 1% at 25.9% chord Source UIUC Airfoil Coordinates Database