ACTA AERONAUTICAET ASTRONAUTICA SINICA >
Panel flutter characteristics on shock wave/boundary layer interaction based on fluid⁃structure coupling
Received date: 2022-03-01
Revised date: 2022-03-21
Accepted date: 2022-04-06
Online published: 2022-04-12
Supported by
National Natural Science Foundation of China(52006099);the Fundamental Research Funds for the Central Universities(30920021102)
To analyze the aeroelastic stability of the flexible panel in shock wave/boundary layer interaction and its influence on flow separation，a developed fluid-structure coupling solver is used to numerically simulate the vibration response and flow characteristics of the flexible panel at different shock impingement locations. The geometrically nonlinear equations of the flexible panel are solved by the finite difference method，Navier-Stokes equations based on the finite volume method，and MUSCL and AUSMPW+ schemes are used for the discretization of convective flux. The conventional serial staggered algorithm is adopted for the fluid-structure interaction. The results exhibit that the vibration displacement of the panel increases first and then decreases，and reaches a stable flutter state after several oscillation cycles，with a second-order vibration mode. The deformation of the panel is asymmetric relative to the shock impingement location. The amplitude of the front part of the panel is always smaller than that of the rear part of the panel. The shock position can significantly change the flutter amplitude，frequency，and separation zone length of the panel. When the shock impingement location is close to both ends of the panel，the vibration of the panel finally converges with the change of the shock impact position. For shock impingement location xi /a=0.35，the panel flutter can effectively suppress flow separation in shock wave/boundary layer interaction.
Weijia LIU , Yingkun LI , Xiong CHEN , Chunlei LI . Panel flutter characteristics on shock wave/boundary layer interaction based on fluid⁃structure coupling[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2023 , 44(6) : 127085 -127085 . DOI: 10.7527/S1000-6893.2022.27085
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