Shock Train Structures in Rectangular Ducts

Gnani, F., Zare-Behtash, H. , White, C. and Kontis, K. (2019) Shock Train Structures in Rectangular Ducts. In: 31st International Symposium on Shock Waves, Nagoya, Japan, 09-14 Jul 2017, pp. 769-776. ISBN 9783319910161 (doi:10.1007/978-3-319-91017-8_96)

Full text not currently available from Enlighten.

Abstract

The deceleration of a supersonic flow to subsonic velocity inside a high-speed engine occurs through a series of shock waves, known as a shock train. The generation of such a flow structure is due to the interaction between the shock waves and the boundary layer inside a long duct. This phenomenon is frequently encountered in a variety of internal flow fields where a shock wave interacts with the boundary layer including air-breathing engines, high-speed wind tunnel diffusers, and supersonic compressors and ejectors. The present study investigates the complex SBLI phenomenon encountered in a Mach 2 shock train through numerical analysis.

Item Type:Conference Proceedings
Status:Published
Refereed:Yes
Glasgow Author(s) Enlighten ID:Kontis, Professor Konstantinos and White, Dr Craig and Gnani, Francesca and Zare-Behtash, Dr Hossein
Authors: Gnani, F., Zare-Behtash, H., White, C., and Kontis, K.
Subjects:Q Science > Q Science (General)
Q Science > QC Physics
T Technology > T Technology (General)
College/School:College of Science and Engineering > School of Engineering > Aerospace Sciences
ISBN:9783319910161
Published Online:03 April 2019

University Staff: Request a correction | Enlighten Editors: Update this record