TY - CONF
T1 - Analysis of unsteady hypersonic shock boundary layer interactions
AU - Tumuklu, Ozgur
AU - Sawant, Saurabh S.
AU - Levin, Deborah A.
AU - Theofilis, Vassilis
N1 - Funding Information:
The research of O.T. and D.A.L. is being supported by the Air Force Office of Scientific Research through AFOSR Grant No. FA9550-11-1-0129 with a subcontract Award No.2010-06171-01 to UIUC. O.T. and D.A.L. are also grateful for the computational resource provided on ERDC Topaz and Onyx, AFRL Thunder and Centennial. The work of V.T. is sponsored by the Air Force Office of Scientific Research, Air Force Material Command, USAF, under Grant No. FA9550-15-1-0387 Global transient growth mechanisms in high-speed flows with application to the elliptic cone, and Grant No. FA9550-17-1-0115 Global Modal and NonModal Instability Analyses of Shock-Induced Separation Bubbles, with V.T. as Principal Investigator and Dr. Ivett Leyva as Program Officer.
Publisher Copyright:
Copyright © IACAS 2020 - 60th Israel Annual Conference on Aerospace Sciences. All rights reserved.
PY - 2020
Y1 - 2020
N2 - A shock dominated separated laminar hypersonic flow over a double cone geometry was investigated by analyzing unsteady direct simulation Monte Carlo signals with the residuals algorithm for a unit Reynolds number of 3.74×105 m−1 at a Mach number of 16. To investigate the origin of the striations in the bow shock observed in the amplitude functions, the momentum density was decoupled into thermal and acoustic parts using Doak's momentum potential theory. The spatial distribution of the acoustic and thermal fields shows alternating patterns, especially in the vicinity of the separation zone and the triple point. The thermal component of the momentum density was found to be large at the cone shoulder at later times due to a Kelvin-Helmholtz instability.
AB - A shock dominated separated laminar hypersonic flow over a double cone geometry was investigated by analyzing unsteady direct simulation Monte Carlo signals with the residuals algorithm for a unit Reynolds number of 3.74×105 m−1 at a Mach number of 16. To investigate the origin of the striations in the bow shock observed in the amplitude functions, the momentum density was decoupled into thermal and acoustic parts using Doak's momentum potential theory. The spatial distribution of the acoustic and thermal fields shows alternating patterns, especially in the vicinity of the separation zone and the triple point. The thermal component of the momentum density was found to be large at the cone shoulder at later times due to a Kelvin-Helmholtz instability.
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M3 - Paper
AN - SCOPUS:85091427392
SP - 1309
EP - 1319
T2 - 60th Israel Annual Conference on Aerospace Sciences, IACAS 2020
Y2 - 4 March 2020 through 5 March 2020
ER -