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Numerical studies on uncontrolled and controlled shock wave/boundary layer interactions in hypersonic intake

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Abstract

Understanding the phenomenon of Shock Wave/Boundary Layer Interaction (SBLI) is critical in developing hypersonic aircraft as it is associated with several penalties, such as huge total pressure loss, boundary layer separation, tremendous temperature rise, fluctuating pressure, and thermal load. The consequences become severe, particularly at hypersonic speeds. Thus, it is essential to control the occurrence of SBLIs to minimize these repercussions. With this in mind, the current study numerically investigates the efficacy of an array of Micro-Vortex Generators (MVGs) placed upstream and at the interaction region in the Mach 5.7 intake. The computational analysis was performed using the finite volume solver Ansys fluent and a 3-dimensional numerical model. MVGs of three different heights (0.5 mm, 0.7 mm, and 1.0 mm) were considered to understand the detailed impact of MVGs height on controlling interactions. The steady-state analysis was carried out using shear stress transport (SST) k–ω turbulence model. Besides, Delayed Detached Eddy Simulation (DES) combined with SST k-omega is specifically considered for unsteady analysis to observe the flow evolution. The quantitative and qualitative analysis has been conducted by examining the static pressure and velocity distributions over the ramp surface and visualizing the shock structures. A maximum of 9.84% reduction in wall static pressure is observed for the MVGs of 1.0 mm height when stationed at the interaction region. The MVGs of 0.7 mm height, placed upstream of the interaction region, are proved to be more efficient than other MVGs. However, pressure recovery and turbulence intensity are maximum for 0.5 mm MVGs, when deployed upstream of the interaction zone.

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All the data and materials used in the study are reported in the article itself.

Abbreviations

SBLIs:

Shock wave/boundary layer interactions

MVGs:

Micro-vortex generators

SST:

Shear stress transport

SBVGs:

Sub-boundary layer vortex generators

3-D:

3-Dimensional

RANS:

Reynolds averaged Navier–Stokes

M :

Mach number

δ 0 :

Undisturbed boundary layer thickness

p :

Wall static pressure

p ∞ :

Free-stream pressure

s :

Span-wise distance between micro-vortex generators

w :

Width of micro-vortex generators

L :

Total axial length of intake

x :

Axial position on the intake

μ :

Dynamic viscosity

μ 0 :

Reference dynamic viscosity

T :

Static temperature

T 0 :

Reference temperature

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Authors declare that the present study did not receive any funding.

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Authors and Affiliations

  1. Department of Aerospace Engineering, Indian Institute of Technology Kharagpur, Kharagpur, 721302, India

    Dorbala Sai Naga Bharghava, Amit Krishnat Mali & Mrinal Kaushik

  2. Department of Aerospace Engineering, BMS College of Engineering, Bengaluru, 560004, India

    Tamal Jana

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  1. Dorbala Sai Naga Bharghava
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  2. Amit Krishnat Mali
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  4. Mrinal Kaushik
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DSNB investigated the problem, analyzed the data and wrote the first draft. AKM revised the first draft. TJ edited and reviewed the first draft. MK supervised the study and edited the final version.

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Correspondence to Mrinal Kaushik.

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Bharghava, D.S.N., Mali, A.K., Jana, T. et al. Numerical studies on uncontrolled and controlled shock wave/boundary layer interactions in hypersonic intake. AS (2023). https://doi.org/10.1007/s42401-023-00252-3

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