Zijun Yi¹, Dan Xie^2,*

The International Conference on Computational & Experimental Engineering and Sciences, Vol.30, No.2, pp. 1-1, 2024, DOI:10.32604/icces.2024.012704

Abstract Hypersonic aircraft face complex aerodynamic forces and severe aerothermal issues. While aerodynamic and aerothermal empirical solutions exhibit high computational efficiency, they lack precision. Numerical approaches equipped with accuracy but come with high computational costs. To address the contradiction between precision and efficiency, some research on hypersonic unsteady aerodynamic and aerothermal Reduced Order Models (ROMs) was conducted in this study, using Kriging surrogate method.
Meanwhile, hypersonic aircraft typically feature numerous thin-wall structures. The strong coupling of aerodynamic, aerothermal, and elasticity will inevitably lead to aerothermoelastic effects. This study centered on the Thermal Protection System (TPS) panel… More >

Chunxiu Ji¹, Dan Xie^1,*

The International Conference on Computational & Experimental Engineering and Sciences, Vol.24, No.1, pp. 1-2, 2022, DOI:10.32604/icces.2022.08737

Abstract This study has established a reduced order model (ROM) based on spectral proper orthogonal decomposition (SPOD) method in order to proceed an aerothermoelastic response analysis of a hypersonic panel. The two-way coupling between aerothermal and aeroelastic systems is applied [1]. Three aspects of POD-ROM are investigated: 1) the selection of snapshots for POD modes; 2) the comparison between classical POD [2] and SPOD [3]; 3) how to find global POD modes in a parameter space of flight altitude and Mach number. The snapshots are sampled from aerothermoelastic response data via the classical Galerkin method. The… More >