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Open Access

REVIEW

Hypersonic Flow over V-Shaped Leading Edges: A Review of Shock Interactions and Aerodynamic Loads

Xinyue Dong1, Wei Zhao1, Jingying Wang1,2,*, Shiyue Zhang1, Yue Zhou3, Xinglian Yang1, Chunhian Lee1,3
1 School of Nuclear Science, Energy and Power Engineering, Shandong University, Jinan, China
2 Shenzhen Research Institute, Shandong University, Shenzhen, China
3 School of Aeronautic Science and Engineering, Beihang University, Beijing, China
* Corresponding Author: Jingying Wang. Email: email

Fluid Dynamics & Materials Processing https://doi.org/10.32604/fdmp.2026.076238

Received 17 November 2025; Accepted 09 January 2026; Published online 19 January 2026

Abstract

For hypersonic air-breathing vehicles, the V-shaped leading edges (VSLEs) of supersonic combustion ramjet (scramjet) inlets experience complex shock interactions and intense aerodynamic loads. This paper provides a comprehensive review of flow characteristics at the crotch of VSLEs, with particular focus on the transition of shock interaction types and the variation of wall heat flux under different freestream Mach numbers and geometric configurations. The mechanisms governing shock transition, unsteady oscillations, hysteresis, and three-dimensional effects in VSLE flows are first examined. Subsequently, thermal protection strategies aimed at mitigating extreme heating loads are reviewed, emphasizing their relevance to practical engineering applications. Special attention is given to recent studies addressing thermochemical nonequilibrium effects on VSLE shock interactions, and the limitations of current research are critically assessed. Finally, perspectives for future investigations into hypersonic VSLE shock interactions are outlined, highlighting opportunities for advancing design and thermal management strategies.

Keywords

V-shaped leading edges; shock interaction; scramjet; thermochemical nonequilibrium; aerodynamic heating

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