Investigation of the pseudo-shock wave in a two-dimensional supersonic inlet

Hyoung Jin Lee, Bok Jik Lee, Sung Don Kim, In Seuck Jeung*

*Corresponding author for this work

Research output: Contribution to journalArticlepeer-review

2 Scopus citations


This paper describes experimental and numerical investigations into the multiple shock waves/ turbulent boundary layer interaction in a supersonic inlet. The test model has a rectangular shape with an asymmetric subsonic diffuser of 5°. Experiments were conducted to obtain the visualization images and static pressure data by using supersonic wind tunnel. Numerical simulation was performed by solving the RANS equations with the Menter's SST turbulent model. The inflow condition was a free-stream Mach number of 2.5 and a unit Reynolds number of 7.6 × 107/m. Numerical results showed good agreement with the experimental results. Based on this agreement, the flow characteristics which are often very difficult to obtain experimentally alone were analyzed with the aid of numerical simulation. The structures, pressure and velocity distributions, and total pressure loss of the pseudo-shock wave in the supersonic inlet were presented in detail from flow visualization images and static pressures.

Original languageEnglish (US)
Pages (from-to)25-32
Number of pages8
JournalJournal of Visualization
Issue number1
StatePublished - Feb 1 2010


  • Asymmetric diffuser
  • Pseudo-shock wave
  • Shock train
  • Supersonic inlet
  • Visualization

ASJC Scopus subject areas

  • Condensed Matter Physics
  • Electrical and Electronic Engineering


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