ORBi: Emory Michael - Characterizing the operability limits of the HyShot II scramjet through RANS simulations

Reference : Characterizing the operability limits of the HyShot II scramjet through RANS simulations


	Document type :	Scientific congresses and symposiums : Paper published in a book
	Discipline(s) :	Engineering, computing & technology : Mechanical engineering Engineering, computing & technology : Aerospace & aeronautics engineering Physical, chemical, mathematical & earth Sciences : Mathematics
	To cite this reference:	http://hdl.handle.net/2268/96232

Title :	Characterizing the operability limits of the HyShot II scramjet through RANS simulations
Language :	English
Author, co-author :	Emory, Michael [Stanford University > Mechanical Engineering Department > > >]
	Terrapon, Vincent [Center for Turbulence Research, Stanford University > > > >]
	Pecnik, René [Center for Turbulence Research, Stanford University > > > >]
	Iaccarino, Gianluca [Stanford University > Mechanical Engineering Department > > >]
Publication date :	Apr-2011
Main document title :	17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011, Vol. 2; No AIAA 2011-2282
Publisher :	Curran Associates, Inc.
Pages :	1019-1034
Audience :	International
ISBN :	9781617829734
City :	Red Hook
Country :	NY
Event name :	17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference
Event date :	from 11-04-2011 to 14-04-2011
Event organizer :	American Institute for Aeronautics and Astronautics ( AIAA )
Event place (city) :	San Francisco, California
Event country :	USA
Keywords :	[en] HyShot II ; RANS ; Scramjet ; Turbulence ; Uncertainty quantification
Abstract :	[en] Experimental and flight data for hypersonic air-breathing vehicles are both difficult and extremely expensive to obtain, motivating the use of computational tools to enhance our understanding of the complex physics involved. One of the major difficulties in simulating this regime is the interaction between combustion and turbulence, both of which are intrinsically complex processes. This work represents a first attempt at addressing assumptions introduced by physical models representing the turbulent reacting flow on the resulting predictions of the scramjet performance. A combustion model for high-speed flows is introduced and tested for the HyShot II vehicle. A reduced order chemistry model is then derived to investigate the effect of certain chemistry modeling assumptions within the combustion model. These models are used to investigate the unstart of the engine due to thermal choking by increasing the fuel flow rate. It is shown that an abrupt change occurs where a normal shock forms and moves upstream accompanied by a large region of subsonic flow. Additionally scalar metrics are described which are used as early indicators of unstart, to formulate safe operating limits for the scramjet engine.
Funders :	United States Department of Energy (DoE)
Name of the research project :	Predictive Science Academic Alliance Program (PSAAP)
Target :	Researchers ; Professionals ; Students
Permalink :	http://hdl.handle.net/2268/96232

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