Shock / boundary-layer interaction control using three-dimensional bumps in supersonic engine inlets

H. Ogawa, H. Babinsky

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

5 Citations (Scopus)


The effects of three dimensional bump control on separated shock-wave / boundarylayer interactions have been investigated experimentally at M = 1.5, aiming to reduce total pressure losses incurred by strong normal shock / boundary-layer interactions. Such a situation occurs, for example, inside mixed-compression supersonic engine inlets or on external-compression inlets. Various bump configurations have been tested and their effects have been evaluated in various aspects such as total pressure recovery and boundary-layer thickness. Without control, the normal shock caused a region of relatively two-dimensional separation. Three-dimensional bumps commonly broke up this separation into individual regions of attached and separated flow, giving an overall reduction of the magnitude of separation. Fairly two-dimensional λ-shock structures and streamwise vortex pairs have been observed in all tested configurations. A configuration comprising multiple long, high, narrow rounded bumps has demonstrated the best performance, producing an appreciable total pressure saving as much as 30% owing to a λ-shock benefit with minimum viscous penalty from localised separation.

Original languageEnglish
Title of host publication46th AIAA Aerospace Sciences Meeting and Exhibit
PublisherAmerican Institute of Aeronautics and Astronautics Inc.
ISBN (Print)9781563479373
Publication statusPublished - Jan 1 2008
Externally publishedYes

Publication series

Name46th AIAA Aerospace Sciences Meeting and Exhibit

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering


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