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Confinement effects in shock wave/turbulent boundary layer interactions through wall-modelled large-eddy simulations

Published online by Cambridge University Press:  03 October 2014

Iván Bermejo-Moreno ,
Laura Campo ,
Johan Larsson ,
Julien Bodart ,
David Helmer  and
John K. Eaton
Iván Bermejo-Moreno*
Affiliation:
Center for Turbulence Research, Stanford University Stanford, CA 94305, USA
Laura Campo
Affiliation:
Department of Mechanical Engineering, Stanford University, Stanford, CA 94305, USA
Johan Larsson
Affiliation:
Center for Turbulence Research, Stanford University Stanford, CA 94305, USA
Julien Bodart
Affiliation:
Center for Turbulence Research, Stanford University Stanford, CA 94305, USA
David Helmer
Affiliation:
Department of Mechanical Engineering, Stanford University, Stanford, CA 94305, USA
John K. Eaton
Affiliation:
Department of Mechanical Engineering, Stanford University, Stanford, CA 94305, USA
*
†Email address for correspondence: ibermejo@stanford.edu
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Abstract

We present wall-modelled large-eddy simulations (WLES) of oblique shock waves interacting with the turbulent boundary layers (TBLs) (nominal $\def \xmlpi #1{}\def \mathsfbi #1{\boldsymbol {\mathsf {#1}}}\let \le =\leqslant \let \leq =\leqslant \let \ge =\geqslant \let \geq =\geqslant \def \Pr {\mathit {Pr}}\def \Fr {\mathit {Fr}}\def \Rey {\mathit {Re}}\delta _{99}=5.4\ \mathrm{mm}$ and ${\mathit{Re}}_{\theta }\approx 1.4\times 10^4$) developed inside a duct with an almost-square cross-section ($45\ \mathrm{mm}\times 47.5\ \mathrm{mm}$) to investigate three-dimensional effects imposed by the lateral confinement of the flow. Three increasing strengths of the incident shock are considered, for a constant Mach number of the incoming air stream $M\approx 2$, by varying the height (1.1, 3 and 5 mm) of a compression wedge located at a constant streamwise location that spans the top wall of the duct at a 20° angle. Simulation results are first validated with particle image velocimetry (PIV) experimental data obtained at several vertical planes (one near the centre of the duct and three near one of the sidewalls) for the 1.1 and 3 mm-high wedge cases. The instantaneous and time-averaged structure of the flow for the stronger-interaction case (5 mm-high wedge), which shows mean flow reversal, is then investigated. Additional spanwise-periodic simulations are performed to elucidate the influence of the sidewalls, and it is found that the structure and location of the shock system, as well as the size of the separation bubble, are significantly modified by the lateral confinement. A Mach stem at the first reflected interaction is present in the simulation with sidewalls, whereas a regular shock intersection results for the spanwise-periodic case. Low-frequency unsteadiness is observed in all interactions, being stronger for the secondary shock reflections of the shock train developed inside the duct. The downstream evolution of secondary turbulent flows developed near the corners of the duct as they traverse the shock system is also studied.

JFM classification

Compressible Flows: Compressible boundary layers Compressible Flows: Shock waves Turbulent Flows: Turbulent boundary layers
Type
Papers
Information
Journal of Fluid Mechanics , Volume 758 , 10 November 2014 , pp. 5 - 62
Copyright
© 2014 Cambridge University Press 

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Footnotes

‡

Present address: Department of Mechanical Engineering, University of Maryland, USA.

§

Present address: Université de Toulouse, ISAE, France.

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