Visualization of hypersonic incident shock wave boundary layer interaction

Qing-hu, Zhang; Zhu, Zhaojie; Lin, Jiang; Futian, Xie; Zhong, Jingjun

doi:10.1007/s12650-019-00622-0

J Vis

2020

DOI: 10.1007/s12650-019-00622-0

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Visualization of hypersonic incident shock wave boundary layer interaction

Zhang Qing-hu

Zhaojie Zhu

Jiang Lin

et al.

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Cited by 4 publications

References 10 publications

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Visualization study of perturbations induced by plasma actuators and its effect on shock wave/boundary-layer interaction

Tian¹,

Wang²,

Gan³

et al. 2022

J Vis

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Surface arc plasma actuator array is used to control the shock wave/boundary-layer interaction in a Ma = 2 flow. Two types of interaction are examined. The flow topology of Surface arc plasma actuator array operating at high-frequency is firstly visualized via particle laser scattering (PLS) technique. The results show that two typical flow structures are observed in the discharging process: the thermal gas bubble and the trailing vortices. The high-frame low-exposure schlieren results for flow visualization indicate a significant separation inhibition in both experiments due to an improvement in the mixture upstream of the interaction region and promoting more turbulent structure into the boundary layer. In the baseline, the separation shock oscillates in a low-frequency mode. When plasma actuation is turned on, the spectra change dramatically when compared to the baseline condition without control. There is an apparent frequency shift for separation shock. Graphical abstract

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Visualization study of perturbations induced by plasma actuators and its effect on shock wave/boundary-layer interaction

Tian¹,

Wang²,

Gan³

et al. 2022

J Vis

View full text Add to dashboard Cite

show abstract

Recent advances in the shock wave/boundary layer interaction and its control in internal and external flows

et al. 2020

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Generalized prediction for self-starting performance of two-dimensional hypersonic inlets

Yang,

Xie,

et al. 2024

Physics of Fluids

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The acceleration self-starting performance of a hypersonic inlet is pivotal for ensuring the stable operation of a scramjet. While the geometric configuration of the internal contraction section (ICS) considerably influences the inlet's self-starting performance, the current prediction model solely considers the internal contraction ratio. To encompass the entire geometric configuration's influence on ICS, a generalized prediction model for the acceleration self-starting Mach number of critical hard unstart two-dimensional hypersonic inlets is proposed. This model calculates the theoretical reattachment pressure rise of the main separation bubble within the actual unstarted flow structure of the hypersonic inlet. Additionally, it computes the theoretical pressure rise assuming the main separation bubble is in a critical state. By comparing these pressures, the model evaluates whether the main separation bubble can be sustained under given incoming flow conditions, predicting the self-starting Mach number. This modeling approach offers broad adaptability to various ICS configurations and incoming flow Reynolds numbers. Each step of the prediction model and the final computational results underwent rigorous evaluation through unsteady numerical simulations. Remarkably, the prediction results demonstrated exceptional alignment with simulation outcomes, surpassing the accuracy of previous prediction methods.

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Visualization of hypersonic incident shock wave boundary layer interaction

Cited by 4 publications

References 10 publications

Visualization study of perturbations induced by plasma actuators and its effect on shock wave/boundary-layer interaction

Visualization study of perturbations induced by plasma actuators and its effect on shock wave/boundary-layer interaction

Recent advances in the shock wave/boundary layer interaction and its control in internal and external flows

Generalized prediction for self-starting performance of two-dimensional hypersonic inlets

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