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.

(fx79l120-il) FX 79-L-120		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 79-L-120 symmetrical airfoil Max thickness 12.1% at 33.9% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database
(e637-il) EPPLER 637 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E637 airfoil Max thickness 12.1% at 27.6% chord Max camber 3.6% at 23.6% chord Source UIUC Airfoil Coordinates Database
(e361-il) EPPLER 361 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E361 rotorcraft airfoil Max thickness 12.1% at 37.1% chord Max camber 1.7% at 27.4% chord 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 Source UIUC Airfoil Coordinates Database
(marske7-il) RONCZ LOW DRAG FLYING WING AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Roncz/Marske-7 low drag flying wing airfoil Max thickness 12.1% at 42.8% chord Max camber 2.8% at 39.1% chord Source UIUC Airfoil Coordinates Database

(naca0012h-sa) NACA0012H for VAWT from Sandia report SAND80-2114		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	Modified Naca 0012 airfoil for Sandia VAWT tests Max thickness 12.2% at 22.5% chord Max camber 0% at 0% chord Source Sandia National Laboratories
(cast102-il) CAST 10-2/DOA 2 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CAST 10-2/DOA 2 transonic airfoil Max thickness 12.2% at 45.4% chord Max camber 1.5% at 69.4% chord Source UIUC Airfoil Coordinates Database
(npl9627-il) NPL 9627 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NPL 9627 rotorcraft airfoil Max thickness 12.2% at 31% chord Max camber 0.9% at 40.4% chord Source UIUC Airfoil Coordinates Database
(e360-il) EPPLER 360 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E360 rotorcraft airfoil Max thickness 12.2% at 36.9% chord Max camber 1.6% at 27.2% chord Source UIUC Airfoil Coordinates Database
(cr1-il) CURTISS CR-1 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Curtiss CR-1 general aviation airfoil Max thickness 12.2% at 24% chord Max camber 4.7% at 42% chord Source UIUC Airfoil Coordinates Database