Drag reduction in transonic shock-wave/boundary-layer interaction using porous medium: a computational study

Roy, Shobhan; Sandhu, Jatinder Pal Singh; Ghosh, Santanu

doi:10.1007/s00193-021-01009-7

Cited by 8 publications

(4 citation statements)

References 59 publications

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“…99 Results of experimental and numerical investigations of supersonic flows around cylinders with porous frontal inserts are reported by Mironov et al 100 Possibilities of drag control are studied for both external and internal heating. Roy et al 101 have carried out a computational study (by RANS) to assess the effectiveness of a porous medium as a control device suitable for reducing the drag caused by a shock wave/boundary layer interaction at transonic speeds. The authors point out that the reduction in overall drag is achieved via recirculation inside the porous medium, which primarily weakens the shock structure and hence reduces the wave drag.…”

Section: Classification and Description Of Flow Control Methodsmentioning

confidence: 99%

“…98 Recently, porous materials are also being employed in aerodynamics for supersonic flow control. [99][100][101] By blowing through, heating or cooling the porous insert material it is possible to ''virtually'' change the body shape and influence its wave drag. The problem of cooling a supersonic aircraft by ''weak'' blowing through porous surface is numerically addressed by Garaev and Mukhametzyanov.…”

Section: Semi-active Flow Controlmentioning

confidence: 99%

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Current state and future trends in boundary layer control on lifting surfaces

Svorcan

Wang

Griffin

2022

Advances in Mechanical Engineering

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Successful flow control may bring numerous benefits, such as flow stabilization, flow reattachment, separation delay, drag reduction, lift increase, aerodynamic performance improvement, energy efficiency increase, shock delay or weakening, noise reduction, etc. For these purposes, many different flow control devices, which can be classified as passive, semi-active and active, have been designed and tested. This review paper aims to highlight the most promising and commonly employed boundary layer control methods as well as outline their potential in specific applications in aerospace and energy engineering. Referenced studies, performed on various geometries (flat plates, channels, airfoils, wings, blades, cylinders), are primarily numerical or experimental. Although enhanced aerodynamic performance is achieved in many cases, further research is required to draw general conclusions. This paper aims to demonstrate that, in the future, we may expect further developments of flow control actuators, as well as their increased application.

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Section: Classification and Description Of Flow Control Methodsmentioning

confidence: 99%

Section: Semi-active Flow Controlmentioning

confidence: 99%

Current state and future trends in boundary layer control on lifting surfaces

Svorcan

Wang

Griffin

2022

Advances in Mechanical Engineering

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“…The transpiration law included in a RANS in-house flow solver yielded accurate numerical results in terms of streamwise pressure distribution, streamwise velocity profiles, boundary layer thickness or Mach contours compared to the experimental data. Roy et al [27] performed a 2D computational study on a porous medium as an alternative passive control strategy to the above-mentioned cavity with a perforated plate. By means of state-state RANS computations with Menter's SST turbulence closure model, the study revealed a maximum of 13% reduction in total drag.…”

Section: Introductionmentioning

confidence: 99%

Effects of Perforated Plates on Shock Structure Alteration for NACA0012 Airfoils

Gall,

Dumitrescu,

Drăgan

et al. 2024

Inventions

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This research investigated a passive flow control technique to mitigate the adverse effects of shock wave–boundary layer interaction on a NACA 0012 airfoil. A perforated plate with a strategically positioned cavity beneath the shock wave anchoring spot was employed. Airfoils with perforated plates of varying orifice sizes (ranging from 0.5 to 1.2 mm) were constructed using various manufacturing techniques. Experimental analysis utilized an “Eiffel”-type open wind tunnel and a Z-type Schlieren system for flow visualization, along with static pressure measurements obtained from the bottom wall. Empirical observations were compared with steady 3D density-based numerical simulations conducted in Ansys FLUENT for comprehensive analysis and validation. The implementation of the perforated plate induced a significant alteration in shock structure, transforming it from a strong normal shock wave into a large lambda-type shock. The passive control case exhibited a 0.2% improvement in total pressure loss and attributed to the perforated plate’s capability to diminish the intensity of the shock wave anchored above. Significant fluctuations in shear stress were introduced by the perforated plate, with lower stress observed in the plate area due to flow detachment from cavity blowing. Balancing shock and viscous losses proved crucial for achieving a favorable outcome with this passive flow control method.

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“…A portion of the available energy is converted into internal energy so that the shock wave intensity and thus the impact loading on the downstream components are reduced. In practical engineering applications, porous barriers have significant potential in mitigating the damage caused by shock waves [1][2][3][4][5]. The shock-induced damage or influence happens in many situations such as the influence of explosion waves on the stability of corridor structures in mine tunnels or oil wells [6,7], the damage of shock waves in a high-speed train tunnel to ancillary facilities [8,9], the sonic boom problem caused by supersonic aircraft breaking through the sound barrier [10,11], etc.…”

Section: Introductionmentioning

confidence: 99%

Numerical Study of Air Flow Induced by Shock Impact on an Array of Perforated Plates

Zhang

Feng

Sun

et al. 2021

Entropy

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This study is focused on the propagation behavior and attenuation characteristics of a planar incident shock wave when propagating through an array of perforated plates. Based on a density-based coupled explicit algorithm, combined with a third-order MUSCL scheme and the Roe averaged flux difference splitting method, the Navier–Stokes equations and the realizable k-ε turbulence model equations describing the air flow are numerically solved. The evolution of the dynamic wave and ring vortex systems is effectively captured and analyzed. The influence of incident shock Mach number, perforated-plate porosity, and plate number on the propagation and attenuation of the shock wave was studied by using pressure- and entropy-based attenuation rates. The results indicate that the reflection, diffraction, transmission, and interference behaviors of the leading shock wave and the superimposed effects due to the trailing secondary shock wave are the main reasons that cause the intensity of the leading shock wave to experience a complex process consisting of attenuation, local enhancement, attenuation, enhancement, and attenuation. The reflected shock interactions with transmitted shock induced ring vortices and jets lead to the deformation and local intensification of the shock wave. The formation of nearly steady jets following the array of perforated plates is attributed to the generation of an oscillation chamber for the inside dynamic wave system between two perforated plates. The vorticity diffusion, merging and splitting of vortex cores dissipate the wave energy. Furthermore, the leading transmitted shock wave attenuates more significantly whereas the reflected shock wave from the first plate of the array attenuates less significantly as the shock Mach number increases. The increase in the porosity weakens the suppression effects on the leading shock wave while increases the attenuation rate of the reflected shock wave. The first perforated plate in the array plays a major role in the attenuation of the shock wave.

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Drag reduction in transonic shock-wave/boundary-layer interaction using porous medium: a computational study

Cited by 8 publications

References 59 publications

Current state and future trends in boundary layer control on lifting surfaces

Current state and future trends in boundary layer control on lifting surfaces

Effects of Perforated Plates on Shock Structure Alteration for NACA0012 Airfoils

Numerical Study of Air Flow Induced by Shock Impact on an Array of Perforated Plates

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