Xinyue Dong¹, Wei Zhao¹, Jingying Wang^1,2,*, Shiyue Zhang¹, Yue Zhou³, Xinglian Yang¹, Chunhian Lee^1,3

FDMP-Fluid Dynamics & Materials Processing, Vol.22, No.1, 2026, DOI:10.32604/fdmp.2026.076238 - 06 February 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 More >

Yue Zhou¹, Pengfei Ju^2,3,*

FDMP-Fluid Dynamics & Materials Processing, Vol.16, No.6, pp. 1273-1283, 2020, DOI:10.32604/fdmp.2020.09666 - 17 December 2020

Abstract The effects of the wall emissivity on aerodynamic heating in a scramjet are analyzed. The supersonic turbulent combustion flow including radiation is solved in the framework of a decoupled strategy where the flow field is determined first and the radiation field next. In particular, a finite difference method is used for solving the flow while a DOM (iscrete ordinates method) approach combined with a WSGGM (weighted sum of gray gases) model is implemented for radiative transfer. Supersonic nonreactive turbulent channel flows are examined for a DLR hydrogen fueled scramjet changing parametrically the wall emissivity. The More >

Jingying Wang, Fangzhou Han^*, Li Lei, Chunhian Lee

FDMP-Fluid Dynamics & Materials Processing, Vol.16, No.3, pp. 601-613, 2020, DOI:10.32604/fdmp.2020.09624 - 25 May 2020

Abstract Accurate aerodynamic heating prediction is of great significance to current manned space flight and deep space exploration missions. The temperature in the shock layer surrounding the reentry vehicle can reach up to 10,000 K and result in remarkable thermochemical nonequilibrium, as well as considerable radiative heat transfer. In general, high-temperature flow simulations coupled with thermal radiation require appropriate numerical schemes and physical models. In this paper, the equations governing hypersonic nonequilibrium flow, based on a three-temperature model combined with a thermal radiation solving approach, are used to investigate the radiation effects in the reentry shock… More >