Characterized by the quasi-conically symmetric flow field,κshock wave system,and highly three-dimensional separation structures,the swept shock-wave/boundarylayer interaction(SBLI)induced by sharp fins is one of the ...Characterized by the quasi-conically symmetric flow field,κshock wave system,and highly three-dimensional separation structures,the swept shock-wave/boundarylayer 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.Theλshock 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.展开更多
基金supported by the National Natural Science Foundation of China(Grant No.12302229,and No.12272354)the Youth Talent Support Program of Henan Province(Grant No.2025HYTP025)+1 种基金the Postdoctoral Fellowship Program of CPSF(Grant No.GZC20232400)the Key Research Project Plan of Higher Education Institutions in Henan Province(Grant No.25A590004)。
文摘Characterized by the quasi-conically symmetric flow field,κshock wave system,and highly three-dimensional separation structures,the swept shock-wave/boundarylayer 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.Theλshock 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.
