scispace - formally typeset
Search or ask a question
Author

T. Hiroshima

Bio: T. Hiroshima is an academic researcher from Muroran Institute of Technology. The author has contributed to research in topics: Mach wave & Boundary layer. The author has an hindex of 1, co-authored 1 publications receiving 3 citations.

Papers
More filters
Book ChapterDOI
01 Jan 2005
TL;DR: In this paper, the structure and characteristics of the multiple shock wave/turbulent boundary layer interaction in a Mach 2 supersonic square duct were investigated by numerical simulation and experiment, and good agreements between the numerical analysis and the experiment for the shape of the shock train and wall pressure distribution along the duct were obtained.
Abstract: This paper presents an investigation on the structure and characteristics of the multiple shock wave/turbulent boundary layer interaction in a Mach 2 supersonic square duct by numerical simulation and experiment. The numerical simulation is carried out with the Harten-Yee’s second-order accuracy TVD scheme and the Baldwin- Lomax’s turbulence model. The flow conditions are: free stream Mach number M∞ = 2.0, unit Reynolds number Re∞/m = 2.5xl07m−1, and the flow confinement is δ∞/h = 0.25. Good agreements between the numerical analysis and the experiment for the shape of the shock train and wall pressure distribution along the duct are obtained. Based on these agreements, the flow quantities, which are difficult to obtain by experiment, are analyzed by numerical simulation.

4 citations


Cited by
More filters
Journal ArticleDOI
TL;DR: In this article, the location of the pseudo-shock system is defined in this system of two choked Laval nozzles by the ratio of the critical cross sections, the stagnation pressure loss across the shock system and viscous losses.
Abstract: Detailed numerical and experimental investigations of pseudo-shock systems in a Laval nozzle with parallel side walls are carried out. The location of the pseudo-shock system is defined in this system of two choked Laval nozzles by the ratio of the critical cross sections $${{A}_{2}^*/{A}_{1}^*}$$ , the stagnation pressure loss across the shock system and viscous losses. The wall pressure distributions and high-speed schlieren videos recorded in the experiments are compared to the results of a steady and an unsteady numerical simulation. For the steady case, good agreement is found between the calculated and measured shock structure and pressure distribution along the primary nozzle wall, except for a remaining slight deviation in the shock position. For the unsteady case, in which asymmetric shock configurations are observed, deviations of the results with respect to the stochastic wall attachment of the shock system are given which indicate the necessity of further investigations on that topic.

30 citations

Journal ArticleDOI
TL;DR: In this article, the Reynolds Averaged Navier Stokes simulation (RANS) was used to investigate the flow physics and the sensitivity to modelling assumptions of a multiple shock wave turbulent boundary layer interaction in a rectangular duct (M r = 1.61, R e δ r = 162000 ).

20 citations

Proceedings ArticleDOI
06 Jan 2020

1 citations