Reference : Numerical predictions of the performance in flight of an air-breathing hypersonic vehicl...
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/2268/96218
Numerical predictions of the performance in flight of an air-breathing hypersonic vehicle: HyShot II
English
Iaccarino, Gianluca [Stanford University > Mechanical Engineering Department > > >]
Pecnik, Rene [Center for Turbulence Research, Stanford University > > > > >]
Terrapon, Vincent mailto [Center for Turbulence Research, Stanford University > > > >]
Doostan, Alireza [University of Colorado, Boulder > Aerospace Engineering Sciences > > >]
Nov-2010
Proceedings of the ASME 2010 International Mechanical Engineering Congress & Exposition; No IMECE2010-40186
[en] IMECE 2010
American Society of Mechanical Engineers
Yes
International
9780791838914
New York
NY
ASME 2010 International Mechanical Engineering Congress & Exposition (IMECE 2010)
from 12-11-2010 to 18-11-2010
American Society of Mechanical Engineers (ASME)
Vancouver
Canada
[en] Scramjet ; Uncertainty quantification ; HyShot II
[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.
United States Department of Energy
Predictive Science Academic Alliance Program (PSAAP)
Researchers ; Professionals ; Students
http://hdl.handle.net/2268/96218

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