scholarly journals Parametric Study of Multiple Shock Wave/Turbulent Boundary Layer Interactions with a Reynolds Stress Model

2021 ◽  
Author(s):  
K. Boychev ◽  
G. Barakos ◽  
R. Steijl
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Numerical Simulations ◽  
Wave Boundary Layer ◽  
Wave Boundary ◽  
Multiple Shock

scholarly journals Parametric study of multiple shock-wave/turbulent-boundary-layer interactions with a Reynolds stress model

Shock Waves ◽  
2021 ◽  
Author(s):  
K. Boychev ◽  
G. N. Barakos ◽  
R. Steijl ◽  
S. Shaw
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Reynolds Stress ◽  
Parametric Study ◽  
High Speed ◽  
Computational Study ◽  
Numerical Approach ◽  
Wave Boundary Layer ◽  
Wave Boundary ◽  
Multiple Shock

AbstractThe flow of high-speed air in ducts may result in the occurrence of multiple shock-wave/boundary-layer interactions. Understanding the consequences of such interactions, which may include distortion of the velocity field, enhanced turbulence production, and flow separation, is of great importance in understanding the operating limits and performance of a number of systems, for example, the high-speed intake of an air-breathing missile. In this paper, the results of a computational study of multiple shock-wave/boundary-layer interactions occurring within a high-speed intake are presented. All of the results were obtained using the in-house computational fluid dynamics solver of Glasgow University, HMB3. First simulations of a Mach $$M=1.61$$ M = 1.61 multiple shock-wave/boundary-layer interaction in a rectangular duct were performed. The $$M=1.61$$ M = 1.61 case, for which experimental data is available, was used to establish a robust numerical approach, particularly with respect to initial and boundary conditions. A number of turbulence modelling strategies were also investigated. The results suggest that Reynolds-stress-based turbulence models are better suited than linear eddy-viscosity models. This is attributed to better handling of complex strain, in particular modelling of the corner separation. The corner separations affect the separation at the centre of the domain which in turn alters the structure of the initial shock and the subsequent interaction. Having established a robust numerical approach, the results of a parametric study investigating the effect of Mach number, Reynolds number, and confinement on the baseline solution are then presented. Performance metrics are defined to help characterize the effect of the interactions. The results suggest that reduced flow confinement is beneficial for higher-pressure recovery.

Modeling of controlled shock-wave/boundary-layer interactions in transonic channel flow

AIAA Journal ◽  
2001 ◽  
Vol 39 ◽  
pp. 2293-2301
Author(s):  
R. Benay ◽  
P. Berthouze ◽  
R. Bur
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Channel Flow ◽  
Wave Boundary Layer ◽  
Wave Boundary

Insights in turbulence modeling for crossing-shock-wave/boundary-layer interactions

AIAA Journal ◽  
2001 ◽  
Vol 39 ◽  
pp. 985-995 ◽  
Author(s):  
Frederic Thivet ◽  
Doyle D. Knight ◽  
Alexander A. Zheltovodov ◽  
Alexander I. Maksimov
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Turbulence Modeling ◽  
Wave Boundary Layer ◽  
Wave Boundary

Fluid-Thermal-Structural Interactions in Ramp-Induced Shock-Wave Boundary-Layer Interactions at Mach 6

2021 ◽  
Author(s):  
Antonio Giovanni Schöneich ◽  
Thomas J. Whalen ◽  
Stuart J. Laurence ◽  
Bryson T. Sullivan ◽  
Daniel J. Bodony ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Wave Boundary Layer ◽  
Structural Interactions ◽  
Wave Boundary
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