Flow structure of supersonic flow past backwardfacing step with perpendicular injector

Akiko Matsuo, Masahiko Mizomoto

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

2 Citations (Scopus)

Abstract

Flow structures of supersonic flow past a backward-facing step with perpendicular injector are numerically investigated under the perfect gas condition in two-dimensional space. The incoming main flow is Mach number 2.5 and the injection is sonic jet, located 24mm behind the step. A step height (0, 2, 3, 6mm) and dynamic pressure ratio of the jet flow to the main flow (0.0, 0.2, 0.4, 0.6, 0.8, 1.0) are examined in the calculations. When the injector is far enough for the main flow to recover supersonic, the injection is independent of the effect of the backward-facing step. However, the jet interacts with the recirculation behind the step, the recirculation region expands to the jet. Once the recirculation region expands, the height of the recirculation region is clocsely related with the dynamic pressure ratio. The expansion waves from the step corner change to the compression wave when the height of the recirculation region becomes higher than the step height. For the step height 6mm, the unsteady oscillation appears in the flowfields. The mechanism of the oscillation is numerically clarified in the simulations.

Original languageEnglish
Title of host publication36th AIAA Aerospace Sciences Meeting and Exhibit
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
Publication statusPublished - 1998
Event36th AIAA Aerospace Sciences Meeting and Exhibit, 1998 - Reno, United States
Duration: 1998 Jan 121998 Jan 15

Other

Other36th AIAA Aerospace Sciences Meeting and Exhibit, 1998
CountryUnited States
CityReno
Period98/1/1298/1/15

Fingerprint

supersonic flow
Supersonic flow
flow structure
Flow structure
injectors
backward facing steps
pressure ratio
dynamic pressure
oscillation
jet flow
injection
Mach number
compression waves
oscillations
ideal gas
elastic waves
compression
Gases
gas
simulation

ASJC Scopus subject areas

  • Engineering(all)
  • Space and Planetary Science

Cite this

Matsuo, A., & Mizomoto, M. (1998). Flow structure of supersonic flow past backwardfacing step with perpendicular injector. In 36th AIAA Aerospace Sciences Meeting and Exhibit [AIAA-98-0939] American Institute of Aeronautics and Astronautics Inc, AIAA.

Flow structure of supersonic flow past backwardfacing step with perpendicular injector. / Matsuo, Akiko; Mizomoto, Masahiko.

36th AIAA Aerospace Sciences Meeting and Exhibit. American Institute of Aeronautics and Astronautics Inc, AIAA, 1998. AIAA-98-0939.

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

Matsuo, A & Mizomoto, M 1998, Flow structure of supersonic flow past backwardfacing step with perpendicular injector. in 36th AIAA Aerospace Sciences Meeting and Exhibit., AIAA-98-0939, American Institute of Aeronautics and Astronautics Inc, AIAA, 36th AIAA Aerospace Sciences Meeting and Exhibit, 1998, Reno, United States, 98/1/12.
Matsuo A, Mizomoto M. Flow structure of supersonic flow past backwardfacing step with perpendicular injector. In 36th AIAA Aerospace Sciences Meeting and Exhibit. American Institute of Aeronautics and Astronautics Inc, AIAA. 1998. AIAA-98-0939
Matsuo, Akiko ; Mizomoto, Masahiko. / Flow structure of supersonic flow past backwardfacing step with perpendicular injector. 36th AIAA Aerospace Sciences Meeting and Exhibit. American Institute of Aeronautics and Astronautics Inc, AIAA, 1998.
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