Z. Chen - State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing University of Aeronautics and Astronautics, ۲۱۰۰۱۶ Nanjing, People’s Republic of China
Y. Zhao - State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing University of Aeronautics and Astronautics, ۲۱۰۰۱۶ Nanjing, People’s Republic of China
R. Huang - State Key Laboratory of Mechanics and Control of Mechanical Structures, Nanjing University of Aeronautics and Astronautics, ۲۱۰۰۱۶ Nanjing, People’s Republic of China

A novel reduced order model (ROM) for unsteady hypersonic aerodynamics is developed, which is applicable for the variations of multi-parameters. The key to the developed ROM lies in the CFD-based model reduction of the steady aerodynamic component, which stems from the quasi-steady nature of aerodynamic forces in the hypersonic regime. Concretely, the proper orthogonal decomposition (POD) method, combined with Kriging interpolation, is used to construct the ROM for the steady aerodynamic component; meanwhile the unsteady part is directly obtained from Donov’s third-order piston theory. The new procedure is applied to a three-dimensional low aspect ratio wing (Lockheed F-۱۰۴ Starfighter wing). It is shown that the developed ROM is able to accurately predict the unsteady hypersonic aerodynamic loads over a wide range of different flight conditions compared with the direct CFD computation.

Reduced order model, Proper orthogonal decomposition, Kriging surrogate, Piston theory, dimensional parametric space, Multi