Interaction of a Normal Shock Wave with a Turbulent Boundary Layer in a Supersonic Nozzle

• HONG Jong-Woo

  "Graduate School of Engineering Sciences, Kyushu University"

• KWON Soon-Bum

  "Dept. of Mech. Enginineering, Nat'l Kyung Pook University"

• TAKAHASHI Jun

  "Ishikawajima-Harima Heavy Industries Co., Ltd."

• MATSUO Kazuyasu

  "Graduate School of Engineering Sciences, Kyushu University"

Bibliographic Information

Other Title

• 203 超音速ノズルにおける垂直衝撃波と乱流境界層の干渉

Abstract

A detailed experimental investigation of shock wavelturbulent boundary layer interaction in a supersonic nozzle was carried out using a schlieren visualization and multiple pressure transducers. The chosen Mach numbers at just upstream of shock are 1.37 and 1.60 which show a bifurcated normal shock and a multiple shocks, respectively. The visualization results show nominal variation of shock patterns from a simple normal shock to a pseudo-shock system as increasing flow Mach number. The measurements of wall pressure using multiple transducers and simultaneous sampling method show the propagation of pressure waves caused by shock and boundary layer interaction. In particular, it becomes clear that the upstream moving pressure waves from reattachment point of boundary layer exist in the case of multiple shock case. However, more detailed investigation is required in the case of a single bifurcated shock system.

Journal

• Journal of the Visualization Society of Japan

  Journal of the Visualization Society of Japan 15 (Supplement2), 213-216, 1995

  The Visualization Society of Japan

Details

• CRID: 1390001204618312832
• NII Article ID: 10002673892
• NII Article ID: 130003648504
• NII Book ID: AN10374478
• DOI: 10.3154/jvs.15.supplement2_213
• ISSN: 1884037X
• ISSN: 09164731
• Text Lang: ja
• Data Source:
  • JaLC
  • Crossref
  • CiNii Articles
• Abstract License Flag: Disallowed