Investigation on shock oscillation phenomenon in a supersonic air inlet

Tomohiro Nakayama, Tetsuya Sato, Masahiro Akatsuka, Atsushi Hashimoto, Takayuki Kojima, Hideyuki Taguchi

Research output: Chapter in Book/Report/Conference proceedingConference contribution

8 Citations (Scopus)

Abstract

Inlet buzz, a shock oscillation phenomenon in supersonic air inlets was studied both numerically and experimentally. Following a supersonic wind tunnel test, a computational analysis was implemented on the supersonic air inlet of the "S-engine" which is a sub-scaled pre-cooled turbo jet engine. In the computation, shock oscillation was observed when the mass-flow was limited. The computed frequency and amplitude showed a good agreement with those of the experiment. It was also observed that the inlet buzz was not triggered when the volume of the aft duct was smaller than a certain value.

Original languageEnglish
Title of host publication41st AIAA Fluid Dynamics Conference and Exhibit
PublisherAmerican Institute of Aeronautics and Astronautics Inc.
ISBN (Print)9781600869471
DOIs
Publication statusPublished - 2011
Event41st AIAA Fluid Dynamics Conference and Exhibit 2011 - Honolulu, HI, United States
Duration: 2011 Jun 272011 Jun 30

Publication series

Name41st AIAA Fluid Dynamics Conference and Exhibit

Conference

Conference41st AIAA Fluid Dynamics Conference and Exhibit 2011
CountryUnited States
CityHonolulu, HI
Period11/6/2711/6/30

ASJC Scopus subject areas

  • Fluid Flow and Transfer Processes
  • Energy Engineering and Power Technology
  • Aerospace Engineering
  • Mechanical Engineering

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  • Cite this

    Nakayama, T., Sato, T., Akatsuka, M., Hashimoto, A., Kojima, T., & Taguchi, H. (2011). Investigation on shock oscillation phenomenon in a supersonic air inlet. In 41st AIAA Fluid Dynamics Conference and Exhibit (41st AIAA Fluid Dynamics Conference and Exhibit). American Institute of Aeronautics and Astronautics Inc.. https://doi.org/10.2514/6.2011-3094