Interaction Between a Conical Shock Wave and a Plane Turbulent Boundary Layer

Gai, S. L.; Teh, Soo Lee

doi:10.2514/2.1060

Cited by 17 publications

(5 citation statements)

References 12 publications

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“…Finally, the flow returns to a nearly ZPG condition. It should be noted that the same wall pressure pattern was observed in the experiments of Gai & Teh (2000).…”

Section: Resultssupporting

confidence: 81%

“…This wall pattern is classically associated with the formation of a horseshoe vortex bending in the downstream direction, as is clarified in figure 21( b ). A very similar organization was also recovered in the experiments of Gai & Teh (2000). Visualization in the symmetry plane highlights the presence of two saddle points at the wall (S1 and S2), being respectively the signature of the separation and reattachment point, and, according to the classification of Chong, Perry & Cantwell (1990), two foci of stable type (F1 and F2), separated by a third saddle point (S3).…”

Section: Resultssupporting

confidence: 79%

“…One of the main conclusions was that, even when regular reflection is possible at the leading edge of the interaction zone, transition to Mach reflection will occur somewhere along the spanwise direction. Gai & Teh (2000) experimentally investigated the interaction of the shock wave produced by a conical shock with a planar turbulent boundary layer, at free-stream Mach number 2. By varying the cone opening angles from to , both attached and separated conditions were achieved.…”

Section: Introductionmentioning

confidence: 99%

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Direct numerical simulation of conical shock wave–turbulent boundary layer interaction

et al. 2019

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Direct numerical simulation of the Navier-Stokes equations is carried out to investigate the interaction of a conical shock wave with a turbulent boundary layer developing over a flat plate at free-stream Mach number M ∞ = 2.05 and Reynolds number Re θ ≈ 630, based on the upstream boundary layer momentum thickness. The shock is generated by a circular cone with half opening angle θ c = 25 • . As found in experiments, the wall pressure exhibits a distinctive N-wave signature, with a sharp peak right past the precursor shock generated at the cone apex, followed by an extended zone with favourable pressure gradient, and terminated by the trailing shock associated with recompression in the wake of the cone. The boundary layer behavior is strongly affected by the imposed pressure gradient, with streaks which are locally suppressed in adverse pressure gradient (APG) zones, and which suddenly reform in the downstream region with favourable pressure gradient (FPG). Three-dimensional mean flow separation is only observed in the first APG region associated with formation of a horseshoe vortex, whereas the second APG region features an incipient detachment state, with scattered spots of instantaneous reversed flow. As found in canonical two-dimensional wedge-generated shock/boundary layer interactions, different amplification of the turbulent stress components is observed through the interacting shock system, with approach to isotropic state in APG regions, and to a two-component anisotropic state in FPG.

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“…Finally, the flow returns to a nearly ZPG condition. It should be noted that the same wall pressure pattern was observed in the experiments of Gai & Teh (2000).…”

Section: Resultssupporting

confidence: 81%

Section: Resultssupporting

confidence: 79%

Section: Introductionmentioning

confidence: 99%

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Direct numerical simulation of conical shock wave–turbulent boundary layer interaction

et al. 2019

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“…The general characteristics of shockwave boundary-layer interactions can be found in comprehensive review papers by Dolling 34 and Settles 35 . More particularly, similar to Brosh et al and Hung, highly complex separated flow as the result of interactions between 3D shockwaves and planar and axi-symmetric boundary-layers are also reported by Derunov et al 36 , Gai 37 and Kussoy et al 38 .…”

Section: Multi-body Flow Physicssupporting

confidence: 76%

Aerodynamic interference between high-speed slender bodies

2010

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Significant aerodynamic interference can occur between high-speed bodies in close proximity. A complex flowfield develops where shock and expansion waves from a generator body impinge upon the adjacent receiver body. The pressure and flow angularity changes which occur across these disturbances modify the body aerodynamics. The aim of this research is to quantify the aerodynamic interference effects for multi-body configurations and understand the relevant flow physics.The interference aerodynamics for slender bodies in a supersonic flow were investigated through a parametric wind tunnel study. The receiver bodies were finned and un-finned configurations. The effect of lateral and axial body separations, receiver incidence and the strength of the disturbance field were investigated. Measurements included forces and moments, surface pressures and flow visualisations. Supporting computations using steady-state, viscous predictions provided a deeper understanding of the underlying aerodynamics and flow mechanisms. Good agreement was found Many people have contributed to the completion of this research. I would like to take time to thank them. My supervisor David MacManus for his guidance and help throughout. I would especially like to thank him for the many occasions when he took my work home with him to read and provide feedback during the writing process. I would like to acknowledge the financial support of the UK MOD. The investigation which is the subject of this report was initiated by the Air Systems Department Dstl and was carried out under the terms of Contract No RD025 -1962. Additional funding was also provided through an ESPRC CASE award. I would also like to thank Dstl for the release of experimental data which greatly enhanced this research. Trevor Birch for his constant support and guidance throughout. In particular, I would like to thank him for making arrangements for me to undertake two placements at Dstl. These aided my research and I enjoyed my time at Dstl immensely. Moreover, I would like to also thank Ben Shoesmith and Kristian Petterson who gave up alot of their own time in order to assist me. Their help with IMPNS and Cobalt was particularly useful.

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“…As found in experiments by Hale (2015) and Gai & Teh (2000), the wall pressure shown in figure 8(a) exhibits a distinctive N-wave signature, with a sharp peak right past the precursor shock generated at the cone apex, followed by an extended zone with FPG, and terminated by the trailing shock associated with recompression in the wake of the cone.…”

Section: Identification Of Flow Regimessupporting

confidence: 68%

On wall pressure fluctuations in conical shock wave/turbulent boundary layer interaction

2023

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The structure and the frequency spectra of wall pressure fluctuations beneath a planar turbulent boundary layer interacting with a conical shock wave at Mach number $M_\infty =2.05$ and Reynolds number $\textit {Re}_\theta \approx 630$ (based on the upstream boundary layer momentum thickness) are examined to elucidate the effects of pressure gradient and flow separation on the characteristics of the wall pressure fluctuations, by exploiting a direct numerical simulation database. Upstream of the interaction, in the zero pressure gradient region, wall pressure statistics compare well with canonical compressible boundary layers in terms of fluctuation intensities and frequency spectra. Across the main interaction zone (APG1), the root-mean-square of wall pressure fluctuations becomes very large (corresponding to approximately 173.3 dB), with maximum increase approximately 12.7 dB from the incoming level. In the second adverse pressure gradient zone (APG2), the root-mean-square of wall pressure fluctuations attains a second peak (corresponding to $164.7$ dB), with an increase of 8.4 dB from the upstream level. Both the APG1 and APG2 regions feature a substantial fraction of flow reversal events, which are, however, scattered and interspersed with regions of attached flow. The wall pressure power spectral density exhibits a broadband and energetic low-frequency component associated with the global unsteadiness of the separation bubble/conical shock system. Analysis of the two-point correlations and wavenumber/frequency spectra of wall pressure fluctuations further suggests that the typical eddies become more elongated along the spanwise direction, as the flow in the separated region tends to escape the centreline, and the convection velocity is significantly reduced.

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Interaction Between a Conical Shock Wave and a Plane Turbulent Boundary Layer

Cited by 17 publications

References 12 publications

Direct numerical simulation of conical shock wave–turbulent boundary layer interaction

Direct numerical simulation of conical shock wave–turbulent boundary layer interaction

Aerodynamic interference between high-speed slender bodies

On wall pressure fluctuations in conical shock wave/turbulent boundary layer interaction

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