Analytical reconstruction of axisymmetric curved shock wave/boundary layer interactions

In practical aerodynamic scenarios, interactions between curved shock waves and boundary layers with composite shock curvatures in both streamwise and spanwise directions are encountered more frequently than those induced by planar oblique shocks. To gain a more systematic understanding of this phen...

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Bibliographic Details
Published in:Physics of fluids (1994) 2024-04, Vol.36 (4)
Main Authors: Cheng, Jianrui, Zhang, Tao, Shi, Chongguang, Da, Xingya, Zhu, Chengxiang, You, Yancheng
Format: Article
Language:English
Subjects:
Boundary layer interaction
Compression ratio
Mathematical analysis
Separation
Shock wave interaction
Shock waves
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Summary:In practical aerodynamic scenarios, interactions between curved shock waves and boundary layers with composite shock curvatures in both streamwise and spanwise directions are encountered more frequently than those induced by planar oblique shocks. To gain a more systematic understanding of this phenomenon in physics, internal and external axisymmetric curved shock wave/boundary layer interactions (AC-SBLI) are being studied analytically by establishing the underlying relations within the flow structures. Specifically, based on reconstructing the dominant structures of AC-SBLI as a semi-analytical model, this study focuses on the impacts of shock spanwise curvatures on separation and the mechanism of their action. It reveals that spanwise curvatures affect the separation in both internal and external AC-SBLI, but each exhibits a different influence pattern, emphasizing apparent axisymmetric characteristic. The spanwise curvatures exert influence indirectly by altering the compression ratio and directly by affecting the distribution of streamwise shock intensities. These findings propose a new approach to estimating the flow structures in AC-SBLI, where analyzing the spanwise curvatures will assist with comprehending other more intricate three-dimensional separation phenomena.
ISSN:1070-6631
1089-7666
DOI:10.1063/5.0199292