Reference : Characterizing the operability limits of the HyShot II scramjet through RANS simulations
Scientific congresses and symposiums : Paper published in a book
Physical, chemical, mathematical & earth Sciences : Mathematics
Engineering, computing & technology : Aerospace & aeronautics engineering
Engineering, computing & technology : Mechanical engineering
http://hdl.handle.net/2268/96232
Characterizing the operability limits of the HyShot II scramjet through RANS simulations
English
Emory, Michael [Stanford University > Mechanical Engineering Department > > >]
Terrapon, Vincent mailto [Center for Turbulence Research, Stanford University > > > >]
Pecnik, René [Center for Turbulence Research, Stanford University > > > >]
Iaccarino, Gianluca [Stanford University > Mechanical Engineering Department > > >]
Apr-2011
17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011, Vol. 2; No AIAA 2011-2282
Curran Associates, Inc.
1019-1034
No
International
9781617829734
Red Hook
NY
17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference
from 11-04-2011 to 14-04-2011
American Institute for Aeronautics and Astronautics ( AIAA )
San Francisco, California
USA
[en] HyShot II ; RANS ; Scramjet ; Turbulence ; Uncertainty quantification
[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.
United States Department of Energy (DoE)
Predictive Science Academic Alliance Program (PSAAP)
Researchers ; Professionals ; Students
http://hdl.handle.net/2268/96232

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