Airfoil Tools
Search 1638 airfoils

You have 0 airfoils loaded.
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.

(pw51-pw) PW51		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	Peter Wick. Airfoil for plank model gliders Max thickness 8.9% at 27.5% chord Max camber 1.4% at 27.5% chord Source RC Groups
(s6062-il) S6062 8%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S6062 low Reynolds number airfoil Max thickness 7.9% at 29.4% chord Max camber 1.4% at 43.7% chord Source UIUC Airfoil Coordinates Database
(rg12-il) RG-12		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rolf Girsberger RG 12 airfoil Max thickness 9.3% at 34.4% chord Max camber 1.4% at 34.4% chord Source UIUC Airfoil Coordinates Database
(mh61-il) MH 61 10.26%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 61 for flying wings Max thickness 10.2% at 27.6% chord Max camber 1.4% at 37.3% chord Source UIUC Airfoil Coordinates Database
(hor04-il) ONERA HOR04 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Onera propeller blade airfoils from US Patent 4 Max thickness 4.1% at 33.2% chord Max camber 1.4% at 38.3% chord Source UIUC Airfoil Coordinates Database

(rae5214-il) RAE 5214 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE 5214 transonic airfoil Max thickness 9.7% at 35.5% chord Max camber 1.4% at 69.1% chord Source UIUC Airfoil Coordinates Database
(rae5213-il) RAE(NPL) 5213 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE(NPL) 5213 transonic airfoil Max thickness 10% at 35.5% chord Max camber 1.4% at 69.1% chord Source UIUC Airfoil Coordinates Database
(mh46-il) MH 46 9.1%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 46 for flying wings Max thickness 9.1% at 27.1% chord Max camber 1.4% at 36.9% chord Source UIUC Airfoil Coordinates Database
(rc12n1-il) NASA/LANGLEY RC-12(N)1 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley RC-12(N)1 rotorcraft airfoil Max thickness 12% at 37.4% chord Max camber 1.4% at 30% chord Source UIUC Airfoil Coordinates Database
(m665-il) M6 (65%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M6 (65%) Max thickness 7.8% at 30% chord Max camber 1.4% at 30% chord Source UIUC Airfoil Coordinates Database