Analysis of the post-flutter aerothermoelastic characteristics of hypersonic skin panels using a CFD-based approach




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Peer reviewed



The present work aims to investigate the post-flutter aerothermoelastic behaviours of the hypersonic skin panels by using the integrated aerothermoelastic analysis framework developed in this paper. The aerodynamic loading and heating are computed simultaneously by solving Reynolds-averaged Navier-Stokes equations (RANS). The structural and thermal finite element models of a hypersonic skin panel are built and solved numerically to model the structural dynamics and thermal conduction. An implicit predictor-corrector scheme is employed to address the fluid-thermal-structural interactions. The aerothermoelastic characteristics of a two-dimensional hypersonic panel obtained using both one-way and two-way coupling strategies are systematically compared and discussed. The results show that: 1) The air viscosity delays the onset of flutter significantly, albeit aggravates thermal effect on the flutter instability; 2) The buckled panel can be similarly predicted by both the one-way and two-way coupling strategies. In contrast, the two-way coupling captures shockwave/boundary layer interactions leading to high local temperature; 3) The modal transition is predicted when structural displacement feeds back into the aerothermoelastic analysis. 4) The variation of temperature gradient along the panel thickness is analogous to the time-domain displacement response as revealed by two-way coupling strategy; 5) One-way coupling predicts lower maximum Von Mises stress as compared with the two-way coupling counterpart under the conditions employed in the present study.


The file attached to this record is the author's final peer reviewed version. The Publisher's final version can be found by following the DOI link.


Aerothermoelasticity, Buckling, Transition, Chaos


Quan, E., Xu, M., yao, W., Cheng, X. (2021) Analysis of the post-flutter aerothermoelastic characteristics of hypersonic skin panels using a CFD-based approach. Aerospace Science and Technology, 118, 107076.


Research Institute

Institute of Engineering Sciences (IES)