Numerical investigation of a Mach 6 hypersonic laminar flow on two-dimensional cold-wall compression corners with controlled surface roughness

Giuseppe, Chiapparino,; Stemmer, Christian

doi:10.1016/j.ijheatfluidflow.2022.108937

Cited by 3 publications

(1 citation statement)

References 23 publications

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“…Generally, for hypersonic flow problems, the analysis of the relevant physical parameters is mostly performed when the specific heat capacity is constant (Dong et al , 2006; Zhou et al , 2020; Giuseppe and Christian, 2022; Ding et al , 2023; Liu et al , 2023; Lee et al , 2023). However, in practice, the specific heat capacity is affected by many factors, so it is actually more suitable to be treated as a function of other variables (Anazadehsayed et al , 2017; Huang and Huang, 2017; Hu et al , 2017; Huang and Hu, 2018; Li et al , 2022; Yury et al , 2022; Yan and Zheng, 2023; Zhao et al , 2023).…”

Section: Introductionmentioning

confidence: 99%

Flow and heat transfer analysis of laminar flow in hypersonic aircraft with variable specific heat capacity at small attack angles

Du,

Wang,

Zhang

et al. 2023

HFF

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Purpose As to different angles of attack and nonlinear problems caused by high temperatures in coexisting hypersonic aircraft, people mainly rely on fluid software for research but lack analysis of flow mechanisms. Owing to computational difficulties, few people use numerical algorithms to combine them for discussion. Hence, this study aims to make a deep inquiry into the laminar flow and heat transfer of compressible Newtonian fluid in hypersonic aircraft with small attack angles. Design/methodology/approach In this paper, on the basis of mass, momentum and energy conservation laws, the governing equations of the hypersonic boundary layer are established. Viscosity, specific heat capacity and thermal conductivity are considered nonlinear functions concerning temperature. In virtue of the MacCormack finite difference method, the stationary numerical solutions are solved directly, and the validity of the algorithm is verified. Findings The results demonstrate that at Mach number 5, compared to the 0° attack angle, the maximum temperature near-wall at the 3° attack angle increases by about 25%. An enjoyable phenomenon is discovered, where the position corresponding to the maximum wall shear force shifts back as the attack angle and Mach number increase. The relationship between the near-wall maximum temperature versus attack angle and Mach number is fitted through numerical calculation results. Originality/value Empirical formulas can be used to estimate heat transfer characteristics at small attack angles, which will guide the design of aircraft thermal protection systems.

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