Transitions of shock interactions on V-shaped blunt leading edges

Zhang, Zhe; Li, Zhufei; Yang, Jiming

doi:10.1017/jfm.2020.1117

Cited by 11 publications

(25 citation statements)

References 30 publications

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“…Shock structures near two straight branches are relatively simple. Zhang et al (2021a) proved that the branches can be regarded as swept cylinders. Bow shocks are generated in front of the branches due to their bluntness.…”

Section: Baseline Vsble Simulationmentioning

confidence: 99%

“…Furthermore, Zhang et al. (2019 a , 2021 a ) combined experiments, numerical simulations and theoretical analysis to explore the shock structures around the VSBLE with a wide range of geometric parameters. Among them, the VSBLE with R/r = 3.25 and β = 24° has attracted much attention.…”

Section: Introductionmentioning

confidence: 99%

“…Xiao et al (2018) first extracted the VSBLE configuration from vehicles and defined the main geometric parameters including the half-span angle β, the leading-edge radius r and the crotch radius R. Based on this model, Li et al (2019) and Wang et al (2018) studied the pressure-heat flux correlation and unsteady shock oscillation around the VSBLE. Furthermore, Zhang et al (2019aZhang et al ( , 2021a combined experiments, numerical simulations and theoretical analysis to explore the shock structures around the VSBLE with a wide range of geometric parameters. Among them, the VSBLE with R/r = 3.25 and β = 24°has attracted much attention.…”

Section: Introductionmentioning

confidence: 99%

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Modelling and shock control for a V-shaped blunt leading edge

et al. 2023

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Hypersonic flow on a V-shaped blunt leading edge (VSBLE) at Mach 12 is numerically investigated. A series of self-induced shock–shock interactions and shock wave/boundary layer interactions (SWBLIs) cause extremely high heat flux peaks on the crotch of the VSBLE. Based on these shock structures, a simplified model that divides the flow field into inviscid and viscous areas is constructed. This model can quickly solve the shock interactions and predict the heating/pressure peaks with high accuracy. Furthermore, a shock control bump (SCB) is placed on the SWBLI region to split the strong incident shock into a weaker multi-wave system. The mechanism study of the SCB shows that the inviscid effect significantly reduces the heating/pressure peaks, and the viscous effect suppresses the SWBLI-induced separation. Finally, a VSBLE with SCBs is numerically investigated. The heat flux peak is reduced by 66 % compared to that without the SCBs. The robustness of the SCB under various working conditions is also evaluated. This paper provides an idea for the simplified solution of complex shock interactions and extends the application of the SCB as a thermal protection device in hypersonic flow for the first time.

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Section: Baseline Vsble Simulationmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Modelling and shock control for a V-shaped blunt leading edge

et al. 2023

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“…2018; Zhang et al. 2019; Zhang, Li & Yang 2021), which is typically observed in a hypersonic inward-turning inlet (You 2011; Gollan & Smart 2013; Bisek 2016). It has been found that the detached shock waves generated from the swept blunt leading edges tend to induce complicated shock interactions.…”

Section: Introductionmentioning

confidence: 99%

“…At the junction of the straight branch and the crotch, which is referred to as the elbow by Zhang et al. (2021), the curved shocks ( and ) or compression waves ( and ) are generated along the converging wall and form secondary interactions with the transmitted shocks. When the interaction is an RR, the intersection point is labelled .…”

Section: Introductionmentioning

confidence: 99%

Mach reflection of three-dimensional curved shock waves on V-shaped blunt leading edges

Zhang,

Cheng,

Shi

et al. 2023

J. Fluid Mech.

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Theoretical investigation of the primary Mach reflection (MR) configuration on V-shaped blunt leading edges (VBLEs) forms the focus of this study. By ignoring the secondary interactions, a theoretical method based on a simplified form of the continuity relation is developed to predict the shock configurations, including the detached shock, the Mach stem, the transmitted shock and the triple point. The comparison of the theoretical results with both numerical and previous experimental results shows the reliability of the theoretical approach in predicting shock structures across a wide range of free stream and geometric parameters. The theoretical model provides a detailed comprehension of the occurrence mechanism of inverse MRs on VBLEs and the influence of the free stream and geometric parameters on primary MR configurations. Along with the primary MR configuration, the curved shock or compression waves generated by the crotch are solved and offer insight into the transition from the MR to the regular reflection from the same family (sRR). The increase of the ratio $R/r$ and the free stream Mach number $M_0$ appears to facilitate the transition, while the effect of the half-span angle $\beta$ is non-monotonic. The predicted shock positions allow for the identification of the transition boundary between the primary MR and sRR. It is found that $R/r$ below a threshold (for a set $M_0$ value) produces MR, irrespective of $\beta$ . If this threshold is exceeded, the configuration can transition from the primary MR to sRR and then back to the primary MR as $\beta$ increases.

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