Experiments on aerothermoelastic fluid–structure interaction in hypersonic flow

Daub, Dennis; Willems, Sebastian; Gülhan, Ali

doi:10.1016/j.jsv.2021.116714

Cited by 32 publications

(4 citation statements)

References 38 publications

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“…Thus, it is likely that the low frequency unsteadiness of the SWBLI which is described by the model by Piponniau et al (2009) for a rigid surface, is still present for the flexible panel, but playing a less relevant role in view of the more energetic contributions at higher frequencies. In a recent investigation of a fluid-structure interaction in hypersonic flow, Daub et al (2022) too, recognized that the role of intrinsic SWBLI unsteadiness on the panel dynamics remains unclear. Although additional research is required, another aspect which could influence the SWBLI dynamics for the flexible panel is the presence of compression waves at the front of the panel, which variation in strength is associated with the local slope of the panel and hence changing with the frequency of oscillation of the structure.…”

Section: Discussionmentioning

confidence: 99%

Characterization of shock-induced panel flutter with simultaneous use of DIC and PIV

et al. 2023

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In this experimental study, panel flutter induced by an impinging oblique shockwave is investigated at a freestream Mach number of 2, using the combination of planar particle image velocimetry (PIV) and stereographic digital image correlation (DIC) to obtain simultaneous full-field structural displacement and flow velocity measurements. High-speed cameras are employed to obtain a time-resolved description of the panel motion and the shockwave-boundary layer interaction (SWBLI). In order to prevent interference between the PIV and DIC systems, an optical isolation is implemented using fluorescent paint, dedicated light sources, and camera lens filters. The effect of the panel motion on the SWBLI behavior is assessed, by comparing it with the SWBLI on a rigid wall. The results show that panel oscillations occur with a maximum amplitude of ten times the panel thickness. The dominant frequencies observed in the panel oscillation (424 Hz and 1354 Hz) match the main spectral content of the reflected shockwave position. A further POD analysis of the panel displacement spatial distribution shows that these two frequency contributions are well captured by the first two POD modes, which correspond, respectively, to a first and a third bending mode shape and account for 92% of the total oscillation energy. The fluid-structure coupling is studied by identifying, in the flow, the regions of maximum correlation between the panel displacement and the flow velocity fluctuations. The results obtained prove that the inviscid flow region upstream of the SWBLI is perfectly in phase with the panel oscillation, while the downstream region has a delay of one quarter of the flutter cycle.

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Section: Discussionmentioning

confidence: 99%

Characterization of shock-induced panel flutter with simultaneous use of DIC and PIV

et al. 2023

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“…These experimental findings are supported by numerical studies by Visbal [38] and Ye [39,40], which indicate that the stability of the panel is significantly compromised in the presence of strong shock impingements, leading to the earlier onset of panel flutter. Furthermore, the inclusion of aerodynamic heating considerations is shown to further compromise the stability of flexible panels [41], resulting in greater deformations [34,42].…”

Section: Introductionmentioning

confidence: 99%

Fluid–Structure Interactions between Oblique Shock Trains and Thin-Walled Structures in Isolators

Meng,

Zhao,

Wang

et al. 2024

Aerospace

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Understanding aeroelastic issues related to isolators is pivotal for the structural design and flow control of scramjets. However, research on fluid–structure interactions (FSIs) between thin-walled structures and the isolator flow remains limited. This study delves into the FSIs between thin-walled panels and the isolator flow, as characterized by an oblique shock train, by quantitatively analyzing 11 flow parameters assessing the structural response, separation zones, shock structures, flow symmetry, and performance. The results reveal that an FSI triggers panel flutter under oblique shock train conditions, with the panel shapes exhibiting a combination of first- and second-mode responses, peaking at 0.75 of the panel length. Compared to rigid wall conditions, isolators with a flexible panel at the bottom wall experience downstream movement of the separation zones and shock structures, reduced flow symmetry, and minor changes in performance. Transient fluctuations occur due to the panel flutter. Two flexible panels at the top and bottom walls have a comparatively lesser influence on the averaged parameters but exhibit more violent transient fluctuations. Furthermore, the FSI effects under oblique shock train conditions are contrasted with those under normal shock train conditions. The flutter response under normal shock train conditions is more pronounced, with a larger amplitude and higher frequency, driven by the heightened participation of the first-mode response. The effects of FSIs under normal shock train conditions on the averaged parameters are the opposite (with a larger influence) to those under oblique shock train conditions, with significantly more drastic transient fluctuations. Overall, this study sheds light on the complex and substantial influence of FSIs on the isolator flow, emphasizing the necessity of considering FSIs in future isolator design and development endeavors.

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“…They also investigated the effect of several structural parameters on the shock wave boundary layer induced panel flutter [14]. In addition to these studies, recently, more experiments and numerical studies focus on the fluid-structure coupling of flexible panels with shock turbulent boundary layer interactions [15][16][17][18][19][20][21][22]. Among them, Daub et al [20] observed panel flutter phenomena in the experimental study of fluid-structure interactions between elastic panel and incident shock wave boundary layer interaction.…”

Section: Introductionmentioning

confidence: 99%

“…In addition to these studies, recently, more experiments and numerical studies focus on the fluid-structure coupling of flexible panels with shock turbulent boundary layer interactions [15][16][17][18][19][20][21][22]. Among them, Daub et al [20] observed panel flutter phenomena in the experimental study of fluid-structure interactions between elastic panel and incident shock wave boundary layer interaction. It was identified that the dynamics of the panel were strongly influenced by the thermal state of structure, and the structure failure due to flutter were found in the experiment.…”

Section: Introductionmentioning

confidence: 99%

Numerical study on the nonlinear characteristics of shock induced two-dimensional panel flutter in inviscid flow

Zhou

Wang

et al. 2022

Preprint

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For an aeroelastic system of a two-dimensional elastic panel subjected to an impinging inviscid oblique shockwave, the nonlinear flutter characteristics are affected by many factors such as shock impingement location, cavity pressure and initial perturbation. The effects of the above factors on the variation of system bifurcation type and dynamic behaviors are investigated numerically. A low-fidelity computational method coupled with local piston theory and van Karman plate model, and a high-fidelity computational method coupled with Euler equations and finite element model are used for fluid-structure interaction simulations. Two sets of new findings are unveiled. First, either the variation of shock impingement location or cavity pressure can induce the aeroelastic system to transition between a subcritical bifurcation and a supercritical bifurcation. For some cases, the system bifurcation characteristics exhibit strong sensitivity to these two factors. Second, it is found that in addition to the limit cycle oscillation (LCO) in the form of a combination of the second and third structural modes, multiple stable LCOs due to the coupling of higher-order modes can be triggered by proper initial perturbations. These LCOs are attributed with high frequencies and some of them even have high amplitudes, which indicates the higher risk of structural fatigue failure.

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Experiments on aerothermoelastic fluid–structure interaction in hypersonic flow

Cited by 32 publications

References 38 publications

Characterization of shock-induced panel flutter with simultaneous use of DIC and PIV

Characterization of shock-induced panel flutter with simultaneous use of DIC and PIV

Fluid–Structure Interactions between Oblique Shock Trains and Thin-Walled Structures in Isolators

Numerical study on the nonlinear characteristics of shock induced two-dimensional panel flutter in inviscid flow

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