Exploratory study of shock reflection near an expansion corner

Frank K. Lu, Kung Ming Chung

Research output: Contribution to conferencePaperpeer-review

1 Citation (Scopus)


Experiments were performed at Mach 8 in which a shock was reflected off a low Reynolds number, turbulent boundary layer past an expansion corner. The shock was generated by 2- and 4-deg sharp wedges and the corner was either 2.5 or 4.25 deg. The inviscid shock reflection was one boundary layer thickness ahead or behind the corner or at the corner itself. All interactions were unseparated. The dynamic surface pressure distributions were together with the case of shock reflection on a flat plate. With shock reflection ahead of the corner, the mean surface pressure downstream was attenuated due to the proximity of the corner. With shock reflection downstream of the corner, the surface pressure distribution showed a reduced upstream influence. The highly swept expansion fan produced a surface pressure which rose gently downstream with no minima, in supersonic flows with the same shock-corner separation distance. In of the interactions, an anomalous pressure peak was found downstream. The surface pressure through the interaction exhibited unsteadiness. A peak in the 2-3 times that of the incoming rms value, was found ahead of the shock reflection location. Secondary were also found downstream.

Original languageEnglish
Publication statusPublished - 1993 Jan 1
EventAIAA 23rd Fluid Dynamics, Plasmadynamics, and Lasers Conference, 1993 - Orlando, United States
Duration: 1993 Jul 61993 Jul 9


OtherAIAA 23rd Fluid Dynamics, Plasmadynamics, and Lasers Conference, 1993
Country/TerritoryUnited States

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering
  • Condensed Matter Physics
  • Electrical and Electronic Engineering
  • Engineering (miscellaneous)


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