4.5 Article

Dynamic interaction between shock wave turbulent boundary layer and flexible panel

期刊

JOURNAL OF FLUIDS AND STRUCTURES
卷 113, 期 -, 页码 -

出版社

ACADEMIC PRESS LTD- ELSEVIER SCIENCE LTD
DOI: 10.1016/j.jfluidstructs.2022.103660

关键词

Fluid-structure interaction; Shock-wave boundary layer interaction; Aeroelastic instability; Panel flutter

资金

  1. DoD HPCMP
  2. Ohio Supercomputer Center

向作者/读者索取更多资源

This study investigates the high-speed fluid-structure interaction between a skin panel and a turbulent shock-boundary layer interaction using large eddy simulations. The study compares the fluid and structural responses in different classes of interaction and elucidates the interplay between the shock-boundary layer interaction and the flexible panel using detailed analysis methods.
The high-speed fluid-structure interaction (FSI) occurring between a skin panel and a turbulent shock-boundary layer interaction (SBLI) are investigated with large eddy simulations (LES). The SBLI is comprised of a Mach 4 and unit Reynolds number of 2.375 x 10(7) (/m) flow interacting with an oblique shock of strength p(3)/p(1) approximate to 8.5 and angle sigma approximate to 30 deg. The inviscid point of impingement on the flexible panel occurs near the mid-chord length. The fully clamped rectangular panel has the aspect ratio and non-dimensional panel thickness of b/a = 1.377 and h/a = 0.003, respectively. The strong SBLI induces a large flow separation of length L-sep approximate to 0.7a (or equivalently approximate to 23 delta(in)) with a wide range of turbulent scales, including the characteristic low-frequency unsteadiness. Fluid and structural responses are compared across different classes of interaction, namely: rigid surface; one-way application of SBLI loads to the structure; and two-way interaction between the flow and structure. The interplay between the SBLI and flexible panel is elucidated using detailed analysis that includes proper orthogonal decomposition (POD), dynamic mode decomposition (DMD), and the recently developed Lagrangian modal analysis (LMA) for the deforming meshes. The large panel deflections (similar to 1h) result in structural non-linearity associated with the coupling between bending and stretching of the panel, manifested in terms of increased modal frequencies of the panel deflection. (C) 2022 Elsevier Ltd. All rights reserved.

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