Visualization of Type IV shock–shock interference induced by a cylindrical protuberance mounted normal to a hollow cylinder

Swept shock wave/boundary layer interactions occur widely in the internal and external flows of supersonic and hypersonic aircraft. Based on the conventional S-A turbulence model, this study investigates surface arc plasma actuation for regulating swept shock wave/boundary layer interactions at Mach 2.95 to explore the ability and three-dimensional shock wave/boundary layer interactions control method of plasma actuation. First, the flow control effect is explored in terms of indirect control by applying actuation in the upstream boundary layer or in front of the separation line, and in terms of direct control by applying actuation in the separation region. These three methods all achieve clear control effects. Control results show that the first method is more effective in regulating the wall pressure and friction coefficient, and can improve the friction and heat transfer of the wall in a wide range of flow direction and cone direction. The second method is more effective in regulating separated shock waves. The third aspect is more effective in regulating reattachment region. The associated control mechanisms are then refined. The control effects of the first control method depend on the transmission of vortices, those of the second are based on the virtual surface generated by actuation, and those of the third rely on energy injection. Finally, the application scenarios of the different control methods are determined according to the flow control requirements of aircraft and the corresponding control mechanisms. This study provides a reference method for solving more complex three-dimensional shock boundary layer interaction problems.

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Swept shock wave/boundary layer interaction control based on surface arc plasma

Yang

Zong

Liang

et al. 2022

Physics of Fluids

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Experimental Investigation of a Roughness Element Wake on a Hypersonic Flat Plate

Han

2022

Aerospace

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An experimental investigation was performed on the wake flow field of an isolated roughness element of a flat plate at Mach 6 by employing the nanoparticle-based planar laser scattering (NPLS) approach. The three-dimensional features and causes of the flow field structure were scrutinized by transient flow field images of roughness elements on various planes. The time-resolved NPLS technique was implemented to examine the time evolution characteristics of the wake flow field of roughness elements. In the following, the process of dynamic evolution of large-scale vortex structures in the wake flow field was methodically assessed. Additionally, the influences of roughness element heights on the wake vortex structure were evaluated and the obtained results were compared.

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Visualization of Type IV shock–shock interference induced by a cylindrical protuberance mounted normal to a hollow cylinder

Cited by 2 publications

References 18 publications

Swept shock wave/boundary layer interaction control based on surface arc plasma

Swept shock wave/boundary layer interaction control based on surface arc plasma

Experimental Investigation of a Roughness Element Wake on a Hypersonic Flat Plate

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