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Hypersonic flow over spherically blunted double cones

Published online by Cambridge University Press:  05 June 2020

Jiaao Hao Open the ORCID record for Jiaao Hao [Opens in a new window]  and
Chih-Yung Wen Open the ORCID record for Chih-Yung Wen [Opens in a new window]
Jiaao Hao
Affiliation:
Department of Mechanical Engineering, The Hong Kong Polytechnic University, Kowloon, Hong Kong
Chih-Yung Wen*
Affiliation:
Department of Mechanical Engineering, The Hong Kong Polytechnic University, Kowloon, Hong Kong Interdisciplinary Division of Aeronautical and Aviation Engineering, The Hong Kong Polytechnic University, Kowloon, Hong Kong
*
†Email address for correspondence: [email protected]
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Abstract

A hypersonic shock wave/laminar boundary-layer interaction over a canonical $25{-}55^{\circ }$ double-cone configuration is numerically investigated. A moderate-enthalpy flow of $5~\text{MJ}~\text{kg}^{-1}$ with a Mach number of 9.87 and a unit Reynolds number of $1.5\times 10^{5}~\text{m}^{-1}$ is considered. Special emphasis is given to the influence of leading-edge bluntness. The results indicate that the double-cone flow is insensitive to small bluntness in terms of shock structures, separation region sizes and surface pressure and heat flux distributions. A critical nose radius is observed, beyond which the separation bubble grows dramatically. The numerical data are analysed and interpreted based on a triple-deck formulation. It is shown that the sudden change in flow features is mainly caused by pressure overexpansion on the first cone due to leading-edge bluntness, such that the skin friction upstream of the separation is significantly reduced and the upstream pressure can no longer resist the large adverse pressure gradient induced by shock impingement. An estimation of the critical radius is established based on the pressure correlations of Blick & Francis (AIAA J., vol. 4 (3), 1966, pp. 547–549) for spherically blunted cones. Simulations at a higher enthalpy with the presence of both vibrational relaxation and air chemistry show a similar trend with increasing nose radius. The proposed criterion agrees well with the experimental observations.

JFM classification

Aerodynamics: High-speed flow Boundary Layers: Boundary layer separation Compressible Flows: Shock waves
Type
JFM Papers
Information
Journal of Fluid Mechanics , Volume 896 , 10 August 2020 , A26
Copyright
© The Author(s), 2020. Published by Cambridge University Press

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