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Modeling of near-continuum laminar boundary layer shocks using DSMC

Tumuklu, Ozgur and Levin, Deborah A. and Gimelshein, Sergey F. and Austin, Joanna M. (2016) Modeling of near-continuum laminar boundary layer shocks using DSMC. In: 30th International Symposium on Rarefied Gas Dynamics. AIP Conference Proceedings. No.1786. American Institute of Physics , Melville, NY, Art. No. 050004. ISBN 978-0-7354-1448-8.

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The hypersonic flow of nitrogen gas over a double wedge was simulated by the DSMC method using two-dimensional and three-dimensional geometries. The numerical results were compared with experiments conducted in the HET facility for a high-enthalpy pure nitrogen flow corresponding to a free stream Mach number of approximately seven. Since the conditions for the double wedge case are near-continuum and surface heat flux and size of the separation are sensitive to DSMC numerical parameters, special attention was paid to the convergence of these parameters for both geometries. At the beginning of the simulation, the separation zone was predicted to be small and the heat flux values for the 2-D model were comparable to the experimental data. However, for increasing time, it was observed that the heat flux values and shock profile strongly deviated from the experiment. Investigation of a three-dimensional model showed that the flow is truly three-dimensional and the side edge pressure relief provides good agreement between simulations and the experiment.

Item Type:Book Section
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Austin, Joanna M.0000-0003-3129-5035
Additional Information:© 2016 AIP Publishing LLC. The research is being performed at the University of Illinois Urbana-Champaign is supported by the Air Force Office of Scientific Research through AFOSR Grant No. FA9550-11-1-0129 with a subcontract award number 2010-06171-01 to UIUC. This research is also a part of the Blue Waters sustained-petascale computing project, which is supported by the National Science Foundation (awards OCI-0725070 and ACI-1238993) and the state of Illinois. Blue Waters is a joint effort of the University of Illinois at Urbana-Champaign and its National Center for Supercomputing Applications.
Funding AgencyGrant Number
Air Force Office of Scientific Research (AFOSR)FA9550-11-1-0129
Air Force Office of Scientific Research (AFOSR)2010-06171-01
State of IllinoisUNSPECIFIED
Subject Keywords:Shock-wave boundary layer interactions, hypersonic separated flows, DSMC
Series Name:AIP Conference Proceedings
Issue or Number:1786
Record Number:CaltechAUTHORS:20170105-143010420
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Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:73280
Deposited By: George Porter
Deposited On:06 Jan 2017 16:35
Last Modified:20 May 2021 23:16

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