NUMERICAL SIMULATION OF HYPERSONIC FLUID-STRUCTURE INTERACTION ON CANTILEVER PLATE WITH OSCILLATING SHOCK IMPINGEMENT
Date
2024-03
Journal Title
Journal ISSN
Volume Title
Publisher
I.O.E
Abstract
When an entity surpasses the velocity of sound, it undergoes a process where it compresses
the air molecules preceding it, resulting in the formation of a region characterized
by heightened pressure called a shock wave. When this shock wave encounters a
physical framework, the framework becomes exposed to a load of pressure, potentially
leading to structural deformation. These scenarios, wherein the interaction between a
fluid medium and structures is involved, are effectively tackled through the discipline
of fluid-structure interaction (FSI). In the case of hypersonic vehicles, shock waves
impact the structures of control surfaces, thereby instigating fluid-structure interaction
within said structures. The scope of this study is to carry out a numerical simulation of
Hypersonic Fluid-Structure Interaction on a Cantilever plate with oscillating shock impingement
location using the UNSW Canberra’s HyMAX benchmark test case. The numerical
simulation is carried out in two approaches i.e. Low Fidelity Modeling (LFM)
and High Fidelity Modeling (HFM). In LFM, the problem is modeled based on shockwave
Expansion Theory , Piston Theory and Euler Bernoulli Model. Whereas in HFM,
the problem is solved by coupling a fluid solver, OpenFOAM, with a structural solver,
CalculiX, via a coupling library, preCICE. The shock-generating wedge was given a
predefined oscillating rotating motion with a frequency of 42 Hz.
Description
The power spectra of peak pressure evolution at the cantilever plate show a
dominant spectral peak at 42 Hz and a second peak at 85 Hz. The trailing edge displacement
obtained on the first cycle was 3.15 mm from viscous simulations and 3.01
mm from inviscid simulations, with an error of 1.86 % and 6.2 %, respectively. The
PSD of trailing edge displacement via LFM shows the spectral peak at 42 Hz and 92.7
Hz (an error of 3%).
Keywords
Aeroelasticity, Fluid-structure interaction, Numerical schlieren, Oscillating shock impingement