ORBi: Rothkegel Ide José Ignacio - Interactive boundary layer calculation of separated flows around 2D airfoils

Reference : Interactive boundary layer calculation of separated flows around 2D airfoils


	Document type :	Scientific congresses and symposiums : Paper published in a book
	Discipline(s) :	Engineering, computing & technology : Aerospace & aeronautics engineering
	To cite this reference:	http://hdl.handle.net/2268/94925

Title :	Interactive boundary layer calculation of separated flows around 2D airfoils
Language :	English
Author, co-author :	Rothkegel Ide, José Ignacio [Université de Liège - ULg > Département d'aérospatiale et mécanique > Interactions Fluide-Structure - Aérodynamique expérimentale >]
	Dimitriadis, Grigorios [Université de Liège - ULg > Département d'aérospatiale et mécanique > Interactions Fluide-Structure - Aérodynamique expérimentale >]
Publication date :	27-Jun-2011
Main document title :	Proceedings of the 15th International Forum on Aeroelasticity and Structural Dynamics, IFASD 2011
Pages :	Paper number IFASD-2011-014
On invitation :	No
Audience :	International
Event name :	International Forum on Aeroelasticity and Structural Dynamics, IFASD 2011
Event date :	from 26-06-2011 to 30-06-2011
Event organizer :	Association Aéronautique Astronautique de France (3AF)
	Council of European Aerospace Sciences (CEAS)
	American Institute of Aeronautics and Astronautics
Event place (city) :	Paris
Event country :	France
Keywords :	[en] Aeroelasticity ; Interactive Boundary Layer ; Panel Methods
Abstract :	[en] Stall flutter is an important undesirable phenomenon affecting lifting surfaces such as helicopter and wind turbine blades, but is particularly difficult to model. Existing methodologies are not universally applicable, and have significant limitations concerning applicability, time of computation and accuracy. This paper presents a method that combines interactive boundary layer with point vortex shedding. It is applied to a NACA0012 airfoil, at different angles of attack in the −40◦ < a < 40◦ range, considering a free flow velocity of 20[m/s]. Results are compared to those obtained at the Goldstein Laboratory of the University of Manchester.
Target :	Researchers ; Professionals
Permalink :	http://hdl.handle.net/2268/94925
Other URL :	http://www.ifasd2011.com/

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Restricted access	50 IFASD_2011_014.pdf		Publisher postprint	194.28 kB	Request copy

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