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Heating reduction with shock control for a V-shaped blunt leading edge

Published online by Cambridge University Press:  26 December 2024

Tao Zhang Open the ORCID record for Tao Zhang [Opens in a new window] ,
Luoyu Rao Open the ORCID record for Luoyu Rao [Opens in a new window] ,
Xuhui Zhang ,
Chongguang Shi Open the ORCID record for Chongguang Shi [Opens in a new window] ,
Chengxiang Zhu Open the ORCID record for Chengxiang Zhu [Opens in a new window]  and
Yancheng You Open the ORCID record for Yancheng You [Opens in a new window]
Tao Zhang
Affiliation:
School of Aerospace Engineering, Xiamen University, Xiamen, Fujian 361005, PR China
Luoyu Rao
Affiliation:
School of Aerospace Engineering, Xiamen University, Xiamen, Fujian 361005, PR China
Xuhui Zhang
Affiliation:
China Academy of Aerospace Science and Innovation, Beijing 100176, PR China
Chongguang Shi*
Affiliation:
School of Aerospace Engineering, Xiamen University, Xiamen, Fujian 361005, PR China
Chengxiang Zhu
Affiliation:
School of Aerospace Engineering, Xiamen University, Xiamen, Fujian 361005, PR China
Yancheng You
Affiliation:
School of Aerospace Engineering, Xiamen University, Xiamen, Fujian 361005, PR China
*
†Email address for correspondence: [email protected]
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Abstract

This study investigates the heating issue associated with a V-shaped blunt leading edge (VBLE) in a hypersonic flow. The heat flux generation on the VBLE is highly correlated with the shock interaction configurations in the crotch region, determined by the relative position of the triple point T and the curved shock (CS). The primary Mach reflection (MR), accompanied by a series of secondary shock–shock interactions and shock wave–boundary layer interactions, can produce extremely high heating peaks on the crotch. To configure the shock wave structures and reduce the heat flux, a shock-controllable design approach is developed based on the simplified continuity method. The strategy involves the inverse design of the crotch sweep path, according to the location of the triple point and the contour of the CS. The comparisons between the pre-designed shock configurations and the numerical results demonstrate the reliability of the design approach across various free stream Mach numbers ranging from 6 to 10. A VBLE model designed with the shock configuration of regular reflection from the same family (sRR) at a free stream Mach number of 8 is examined. Under the design conditions, the outermost heat flux peak is reduced by 80 % compared with the baseline case. The heating reduction capabilities of the model under varying free stream Mach numbers and sideslip angles are also evaluated, confirming its robustness under undesigned operating scenarios.

JFM classification

Compressible Flows: Hypersonic Flow Compressible Flows: Shock waves
Type
JFM Papers
Information
Journal of Fluid Mechanics , Volume 1002 , 10 January 2025 , A15
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Copyright
© The Author(s), 2024. Published by Cambridge University Press

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Footnotes

Article updated 7 January 2025.

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