Affiliation of Author(s):College of Aerospace Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016

Teaching and Research Group:High Speed Wind tunnel Laboratory （HSWL)

Journal:Chinese Journal of Aeronautics

Place of Publication:Chinese Society of Aeronautics and Astronautics & Beihang University

Funded by:National Natural Science Foundation of China

Key Words:Boundary layer separation;Compressible flow;Shock train;Oscillating flow;Wind tunnel testing

Abstract:The structure and dynamics of an oblique shock train in a duct model are investigated experimentally in a hypersonic wind tunnel. Measurements of the pressure distribution in front of and across the oblique shock train have been taken and the dynamics of upstream propagation of the oblique shock train have been analyzed from the synchronized schlieren imaging with the dynamic pressure measurements. The formation and propagation of the oblique shock train are initiated by the throttling device at the downstream end of the duct model. Multiple reflected shocks,expansion fans and separated flow bubbles exist in the unthrottled flow, causing three adverse-pressure-gradient phases and three favorable-pressure-gradient phases upstream the oblique shock train. The leading edge of the oblique shock train propagates upstream, and translates to be asymmetric with the increase of backpressure. The upstream propagation rate of the oblique shock train increases rapidly when the leading edge of the

Indexed by:Journal paper

Document Code:http://dx.doi.org/10.1016/j.cja.2017.02.004

Discipline:Engineering

First-Level Discipline:Aeronautical and Astronautical Science and Technology

Document Type:J

Volume:30

Issue:2

Page Number:663-676

Number of Words:6731

ISSN No.:1000-9361

Translation or Not:no

Date of Publication:2017-02-14

Included Journals:SCIE

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