Influence of glow discharge on evolution of disturbance in a hypersonic boundary layer: The effect of first mode

Li, Chi; Zhang, Yunchi; Lee, Cunbiao

doi:10.1063/5.0008457

Cited by 18 publications

(10 citation statements)

References 22 publications

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“…Considering that the amplitude of the second mode is much larger than that of the low-frequency waves, second mode transfers energy to the low-frequency waves through the phase velocity locking mechanism, promoting a rapid increase in the amplitude of the low-frequency waves. This result is consistent with the interaction mechanism experimentally obtained on a flat plate (Li et al 2020). The amplitude of the travelling cross-flow wave is 50 % of that of the low-frequency waves for x between 280 and 370 mm.…”

Section: Instability Interactionsupporting

confidence: 91%

“…The interaction mechanism that transfers energy from the relatively high-frequency second mode to the low-frequency first mode is the phase velocity locking mechanism. This is a generalisation of phase-locking theory that is consistent with the findings of previous studies on the hypersonic boundary layer (Li et al 2020;Zhang et al 2020).…”

Section: Instability Interactionsupporting

confidence: 91%

“…(2017 a ) studied this problem using nonlinear parabolised equation analysis, showing that a phase-locking interaction mechanism first transfers energy from the second mode to low-frequency waves, and then a parametric resonance takes effect. Li, Zhang & Lee (2020) also investigated this phenomenon over a Mach 6 flat plate, which is a condition more similar to that used in this study. The low-frequency waves are identified as the vortical first-mode-like waves and can be enhanced by the second mode through a phase-lock interaction.…”

Section: Resultsmentioning

confidence: 99%

“…Later, Li et al. (2020) and Zhang, Li & Lee (2020) extended the phase-locked mechanism to the interaction of different frequency disturbances, holding that the phase velocity locking mechanism can explain the interaction between the second mode and the first mode, and the second mode can transfer energy to the first mode through the phase velocity locking mechanism. In addition, the phase difference locking mechanism can explain the interaction between the first mode and the second mode, which causes the first mode to transfer energy to the second mode.…”

Section: Analysis and Discussionmentioning

confidence: 99%

“…Here, we adopt the method that Li et al. (2020) and Zhang et al. (2020) used to study the interaction between modes in a flat-plate boundary layer to analyse whether interactions exist between the travelling cross-flow mode and the second mode; the second mode and the first mode; and the travelling cross-flow mode and the first mode.…”

Section: Analysis and Discussionmentioning

confidence: 99%

See 4 more Smart Citations

Boundary layer transition of hypersonic flow over a delta wing

Qiu,

Shi,

Zhu

et al. 2024

J. Fluid Mech.

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Cross-flow transition over a delta wing is systematically studied in a Mach 6.5 hypersonic wind tunnel, employing the Rayleigh scattering flow visualisation, high-speed schlieren and fast-response pressure sensors. Direct numerical simulations and analysis based on linear stability theory under the same flow conditions are applied to analyse the transition mechanism. Three unstable modes are identified: the travelling cross-flow instabilities, the second mode and the low-frequency waves. It is shown that the travelling cross-flow vortices first appear in the cross-flow region near the leading edge of the model. These vortices can modulate the mean profile of the flow, which benefits the growth of second mode. A phase-locked interaction mechanism transfers energy from the cross-flow instabilities to the high-frequency second mode, leading to amplification at the expense of the cross-flow instability. As the second mode grows to a critical amplitude, it triggers a $z$ -type secondary instability within a similar frequency range, which introduces secondary finger-like structures connecting to the cross-flow vortex. It is further found that the generation of these finger-like structures is related to the expansion and compression of the second mode. These finger vortices further evolve along the streamwise direction into low-frequency waves and corresponding hairpin-like structures that finally trigger turbulence. An interaction mechanism likely exists between the secondary instability and the low-frequency waves, since their phase speeds are approaching each other. These observations of the interaction mechanism are consistent with those of previous studies on hypersonic boundary layers (Zhang et al., Phys. Fluids, vol. 32 (7), 2020, 071702; Li et al., Phys. Fluids, vol. 32 (5), 2020, 051701).

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Section: Instability Interactionsupporting

confidence: 91%

Section: Instability Interactionsupporting

confidence: 91%

Section: Resultsmentioning

confidence: 99%

Section: Analysis and Discussionmentioning

confidence: 99%

Section: Analysis and Discussionmentioning

confidence: 99%

See 3 more Smart Citations

Boundary layer transition of hypersonic flow over a delta wing

Qiu,

Shi,

Zhu

et al. 2024

J. Fluid Mech.

Self Cite

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Experimental investigation of supersonic boundary-layer tripping with a spanwise pulsed spark discharge array

Tang

Zong

et al. 2021

J. Fluid Mech.

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In this paper, a pulsed spark discharge plasma actuator array is deployed to control laminar–turbulent transition in a Mach 3.0 flat-plate boundary layer, and the subtle flow structures are visualized by nanoparticle planar laser scattering (NPLS) technique. Results show that the onset location of turbulence can be brought upstream by plasma actuation, corresponding to forced boundary-layer transition. Hairpin vortex packets evolved from the thermal bulbs play a vital role in the breakdown of laminar flow. With the help of a machine learning tool, all the relevant structures induced by plasma actuation are extracted from NPLS images, and a conceptual model of the hairpin vortex generation is proposed, including three stages: production and lift-up of the high-vorticity region, formation of the $\varLambda$ vortex and evolution of the hairpin vortex.

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Influence of glow discharge on evolution of disturbance in a hypersonic boundary layer: The effect of second mode

Zhang

Lee

2020

Physics of Fluids

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This is the companion volume on the effects of artificial disturbance on the transition process of a boundary layer over a flat plate. The artificial disturbance with the frequency in the range of second-mode instability is introduced into the boundary layer by glowing discharge on the surface of the plate. Experiments are performed using Rayleigh-scattering visualization, wall pressure pulsations measurement, and high-frequency schlieren visualization in the Φ300 mm hypersonic quiet wind tunnel at Peking University. It is found that the second-mode instability waves are stimulated remarkably by the artificial disturbance, and the boundary layer transition is triggered effectively. The second-mode instability interacts with the first mode via a phase-lock mechanism, which leads to the rapid amplification of the first mode and the moving forward of transition location.

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Influence of glow discharge on evolution of disturbance in a hypersonic boundary layer: The effect of first mode

Cited by 18 publications

References 22 publications

Boundary layer transition of hypersonic flow over a delta wing

Boundary layer transition of hypersonic flow over a delta wing

Experimental investigation of supersonic boundary-layer tripping with a spanwise pulsed spark discharge array

Influence of glow discharge on evolution of disturbance in a hypersonic boundary layer: The effect of second mode

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