ORBi: Andrianne Thomas - Using the Discrete Vortex Method to Simulate the Stall Flutter Phenomenon

Reference : Using the Discrete Vortex Method to Simulate the Stall Flutter Phenomenon


	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/2268/24446

Title :	Using the Discrete Vortex Method to Simulate the Stall Flutter Phenomenon
Language :	English
Author, co-author :	Andrianne, Thomas [Université de Liège - ULg > Département d'aérospatiale et mécanique > Département d'aérospatiale et mécanique >]
	Dimitriadis, Grigorios [Université de Liège - ULg > Département d'aérospatiale et mécanique > Interactions Fluide-Structure - Aérodynamique expérimentale >]
Publication date :	Jun-2009
Main document title :	Proceedings of the 2009 International Forum on Aeroelasticity and Structural Dynamics
Publisher :	Azimuth Corporation
Pages :	Paper IFASD-2009-025
Peer reviewed :	No
On invitation :	No
Audience :	International
City :	Dayton, Ohio
Country :	USA
Event name :	International Forum on Aeroelasticity and Structural Dynamics, IFASD 2009
Event date :	du 21 juin au 25 juin 2009
Event organizer :	Council of European Aerospace Sciences, American Institute of Aeronautics and Astronautics
Event place (city) :	Seattle, Washington
Event country :	USA
Keywords :	[en] Discrete Vortex Method ; Stall Flutter ; Dynamic Stall
Abstract :	[en] The Discrete Vortex Method (DVM) has been recently used by several researchers in order to simulate the dynamic stall phenomenon on 2D airfoils oscillating at high angles of attack or undergoing stall flutter oscillations. The aim of the present work is to investigate whether such simulations are representative of the true physics governing such oscillation. A DVM method is described and implemented. A basic validation of the method is performed on the case of an impulsively started static airfoil at a low angle of attack. It is shown that the steady state lift value obtained from the DVM method agrees with experimental measurements. Subsequently, a DVM simulation is performed for the case of a NACA 0012 airfoil undergoing symmetric stall flutter oscillations. The simulation results are compared to experimental results. It is shown that, while the general shape of the simulated lift variation with time agrees with the experiment, there are significant mean value and phase differences between experiment and simulation. Several justifications are suggested and improvements to the DVM simulation proposed.
Target :	Researchers ; Professionals
Permalink :	http://hdl.handle.net/2268/24446
Other URL :	http://papers.ifasd2009.com/proceedings

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