ORBi: Iaccarino Gianluca - Numerical predictions of the performance in flight of an air-breathing hypersonic vehicle: HyShot II

Reference : Numerical predictions of the performance in flight of an air-breathing hypersonic vehicl...


	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/2268/96218

Title :	Numerical predictions of the performance in flight of an air-breathing hypersonic vehicle: HyShot II
Language :	English
Author, co-author :	Iaccarino, Gianluca [Stanford University > Mechanical Engineering Department > > >]
	Pecnik, Rene [Center for Turbulence Research, Stanford University > > > > >]
	Terrapon, Vincent [Center for Turbulence Research, Stanford University > > > >]
	Doostan, Alireza [University of Colorado, Boulder > Aerospace Engineering Sciences > > >]
Publication date :	Nov-2010
Main document title :	Proceedings of the ASME 2010 International Mechanical Engineering Congress & Exposition; No IMECE2010-40186
Alternative title :	[en] IMECE 2010
Publisher :	American Society of Mechanical Engineers
Audience :	International
ISBN :	9780791838914
City :	New York
Country :	NY
Event name :	ASME 2010 International Mechanical Engineering Congress & Exposition (IMECE 2010)
Event date :	from 12-11-2010 to 18-11-2010
Event organizer :	American Society of Mechanical Engineers (ASME)
Event place (city) :	Vancouver
Event country :	Canada
Keywords :	[en] Scramjet ; Uncertainty quantification ; HyShot II
Abstract :	[en] The uncertainties inherent to the operating conditions of the Hyshot II scramjet flight test are assessed. In particular, the variability of the pressure prediction in the combustor due to uncertain free stream conditions is investigated using a probabilistic methodology based on stochastic collocation. The uncertainties in Mach number, angle of attack and flight altitude are inferred from pressure measurements in the unfueled combustor using a Bayesian inversion approach. The forward computation relies on a reduced order model that represents the combustion processes in the scramjet combustor. A ground based experimental data set obtained from 1-to-1 model of the HyShot II vehicle with well defined operating conditions is used to validate the non-reacting solver and to calibrate the heat release model for the reacting combustor. The model prediction agrees well with the experimentally acquired flight data. On the other hand, our estimated flight free stream conditions differ from previously published results.
Funders :	United States Department of Energy
Name of the research project :	Predictive Science Academic Alliance Program (PSAAP)
Target :	Researchers ; Professionals ; Students
Permalink :	http://hdl.handle.net/2268/96218

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