Explicit algebraic Reynolds stress model for shock-dominated flows

Vemula, Jagadish Babu; Sinha, Krishnendu

doi:10.1016/j.ijheatfluidflow.2020.108680

Cited by 4 publications

(2 citation statements)

References 34 publications

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“…In addition,  is the specific heat ratio. Due to its widespread in engineering applications, the shock wave has studded intensively in different engineering areas [2], [3], [4], [5]. Moreover, because of their importance in aeronautical applications, recently shock wave has gained inevitable significance.…”

Section: Introductionmentioning

confidence: 99%

Numerical Study of Oblique Shock Wave

Ali

2023

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This study aims to investigate some physical parameters in presence of an oblique shock wave numerically. Computational fluid dynamics has been used to analyze fluid behavior upstream and downstream of the shock wave. To obtain a good resolution, the computational domain is constructed by fine meshing. Due to its wide use in engineering applications, Air has been used as fluid material. A wedge of half-angle q = 22° has been used to intercept the airflow path and founding the oblique shock wave of anglef. For gathering comprehensive information, the air flows have been tested for three Mach numbers, namely slightly higher than 1, slightly higher than two, and slightly higher than three (M1~=1, M2~=2, and M3~=3) and represented as a case (a), (b) and (c) respectively. The continuity equation, momentum equation, and energy equation have been solved numerically. Velocity, turbulent viscosity, total pressure, and total enthalpy have been investigated upstream and downstream of the shockwave for the three different Mach numbers. The results showed that the total pressure downstream of the shock wave was less than that of the upstream shock wave. In addition, the turbulent viscosity area around the object becomes thicker as the Mach numbers become bigger. Also, the total pressure was slightly different for the three different Mach numbers. These behaviors of the above-mentioned parameters are attributed to the shock wave effects. In addition, the oblique shock wave angle f is appeared to be decreased as the Mach number increased.

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Section: Introductionmentioning

confidence: 99%

Numerical Study of Oblique Shock Wave

Ali

2023

basjs

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“…The question as to within what range of governing parameters the results from LIA can be considered reliable is still open (Chen & Donzis 2019). This question has become particularly relevant in recent times, where LIA is being used as a surrogate to numerical simulations in regions of shock waves (Braun, Pullin & Meiron 2019) and LIA-based turbulence models are increasingly being used in practical applications (Sinha, Mahesh & Candler 2005;Pasha & Sinha 2012;Roy, Pathak & Sinha 2018;Vemula & Sinha 2020). Lee et al (1993) studied the interaction of isotropic quasi-incompressible turbulence with a weak shock wave using DNS for 1.05 ≤ M 1 ≤ 1.2.…”

Section: Introductionmentioning

confidence: 99%

A weakly nonlinear framework to study shock–vorticity interaction

2022

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Linear interaction analysis (LIA) is routinely used to study the shock–turbulence interaction in supersonic and hypersonic flows. It is based on the inviscid interaction of elementary Kovásznay modes with a shock discontinuity. LIA neglects nonlinear effects, and hence it is limited to small-amplitude disturbances. In this work, we extend the LIA framework to study the fundamental interaction of a two-dimensional vorticity wave with a normal shock. The predictions from a weakly nonlinear framework are compared with high-order accurate numerical simulations over a range of wave amplitudes ( $\epsilon$ ), incidence angles ( $\alpha$ ) and shock-upstream Mach numbers ( $M_1$ ). It is found that the nonlinear generation of vorticity at the shock has a significant contribution from the intermodal interaction between vorticity and acoustic waves. Vorticity generation is also strongly influenced by the curvature of the normal shock wave, especially for high incidence angles. Further, the weakly nonlinear analysis is able to predict the correct scaling of the nonlinear effects observed in the numerical simulations. The analysis also predicts a Mach number dependent limit for the validity of LIA in terms of the maximum possible amplitude of the upstream vorticity wave.

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Anisotropic SST turbulence model for shock-boundary layer interaction

Raje

Sinha

2021

Computers & Fluids

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Explicit algebraic Reynolds stress model for shock-dominated flows

Cited by 4 publications

References 34 publications

Numerical Study of Oblique Shock Wave

Numerical Study of Oblique Shock Wave

A weakly nonlinear framework to study shock–vorticity interaction

Anisotropic SST turbulence model for shock-boundary layer interaction

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