Aerothermoelastic analysis on the interaction between flexible panels and swept shock-wave/boundary-layer interactions induced by sharp fins

Characterized by the quasi-conically symmetric flow field, λ shock wave system, and highly three-dimensional separation structures, the swept shock-wave/boundary-layer interaction (SBLI) induced by sharp fins is one of the most important phenomena in supersonic flights. An aerothermoelastic analysis is conducted on the interactions between thin-walled panels and swept SBLIs. The results of rigid wall condition, aeroelastic analysis and aerothermoelastic analysis are compared to highlight the significant influence of fluid-thermal-structural interactions on the structure and the flow field of swept SBLIs. The results show that in the aeroelastic analysis, for the material applied to the panel, although a dynamic structural response is observed, the deformation is minor and has a limited influence on the flow field. However, in the aerothermoelastic analysis, the consideration of aerodynamic heating has a significant impact on the structural response and the flow field. The deformation is an order of magnitude larger than that in the aeroelastic analysis with high vibration frequency and various main frequencies at different locations. As a result, the flow field is no longer quasi-conically symmetric. The λ shock wave system and separation structures are completely disrupted by multiple shock and expansion waves induced by the large structural deformation and become much more complex with highly three-dimensional features. This research highlights the significance of investigations on complex three-dimensional aerothermoelastic problems for supersonic flight vehicles.