Dynamic interaction between shock wave turbulent boundary layer and flexible panel

Shinde, Vilas; McNamara, Jack J.; Gaitonde, Datta V.

doi:10.1016/j.jfluidstructs.2022.103660

Cited by 31 publications

(2 citation statements)

References 64 publications

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“…2021; He et al. 2022; Shinde, McNamara & Gaitonde 2022). Moreover, these complex aeroelastic characteristics significantly impact the performance of the vehicles (Bhattrai et al.…”

Section: Introductionmentioning

confidence: 99%

“…Shock phenomena is one of the typical features in hypersonic flow, widely present in both internal and external flow configurations, such as the intricate shock structures found in a scramjet engine inlet (Matsuo, Miyazato & Kim 1999;Urzay 2018). The presence of shock gives rise to an accentuation of the nonlinear and unsteady characteristics of aerodynamic loads, which, in turn, lead to even greater complexity in the aeroelastic characteristics of the panel (Shinde et al 2019;Boyer et al 2021;Brouwer et al 2021;He et al 2022;Shinde, McNamara & Gaitonde 2022). Moreover, these complex aeroelastic characteristics significantly impact the performance of the vehicles (Bhattrai et al 2022;Liu et al 2022).…”

Section: Introductionmentioning

confidence: 99%

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On the aeroelastic bifurcation of a flexible panel subjected to cavity pressure and inviscid oblique shock

Zhang,

Ye,

2024

J. Fluid Mech.

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The aeroelasticity of a panel in the presence of a shock is a fundamental issue of great significance in the development of hypersonic vehicles. In practical engineering, cavity pressure emerges as a crucial factor that influences the nonlinear dynamical characteristics of the panel. This study focuses on the aeroelastic bifurcation of a flexible panel subjected to both cavity pressure and oblique shock. To this end, a computational method is devised, coupling a high-fidelity reduced-order model for unsteady aerodynamic loads with nonlinear structural equations. The solution is meticulously tracked by continuous calculations. The obtained results indicate that cavity pressure plays a pivotal role in determining the bifurcation and stability characteristics of the system. First, the system exhibits hysteresis behaviour in response to the ascending and descending dynamic pressures. The evolution of hysteresis behaviour originates from the phenomenon of cusp catastrophe. Second, variations in cavity pressure induce three types of bifurcation phenomena, exhibiting characteristics akin to supercritical Hopf bifurcation, subcritical Hopf bifurcation and saddle-node bifurcation of cycles. The system's response at the critical points of these bifurcations manifests as long-period asymptotic flutter or explosive flutter. Lastly, the evolution of the dynamical system among these three types of bifurcations is an important factor contributing to the discrepancies observed in certain research results. This study enhances the understanding of the nonlinear dynamical behaviour of panel aeroelasticity in complex practical environments and provides new explanations for the discrepancies observed in certain research results.

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“…2021; He et al. 2022; Shinde, McNamara & Gaitonde 2022). Moreover, these complex aeroelastic characteristics significantly impact the performance of the vehicles (Bhattrai et al.…”

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

On the aeroelastic bifurcation of a flexible panel subjected to cavity pressure and inviscid oblique shock

Zhang,

Ye,

2024

J. Fluid Mech.

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Nonlinear aeroelastic behavior of a panel impinged by oscillating shock

He,

Shi,

Dowell

et al. 2024

Nonlinear Dyn

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The aeroelastic responses and nonlinear behaviors of a two-dimensional panel impinged by an oscillating Mach stem shock are investigated through theoretical analysis. Through the nonlinear descriptors, such as Poincaré maps and Largest Lyapunov exponents, the panel with oscillating shock impingement is found to exhibit multiple responses, including single/multi-periodic limit cycle oscillation, quasiperiodic motion, and chaotic motion. Without altering the in-plane force, which is the principal source of structural nonlinearity, the shock oscillation complicates the nonlinear behaviors of the panel. With shock oscillation, the original divergence instability is transformed into post-divergence limit cycle oscillation, and the flutter response exhibits rich nonlinear characteristics. The effect of initial shock impingement location, shock oscillating amplitude, and shock oscillating frequency are disclosed through the bifurcation diagram, which significantly influences the nonlinear character-

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Fluid structure interactions generated by an oblique shock impinging on a thin elastic panel

Varigonda

Narayanaswamy

2023

Journal of Fluids and Structures

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Dynamic interaction between shock wave turbulent boundary layer and flexible panel

Cited by 31 publications

References 64 publications

On the aeroelastic bifurcation of a flexible panel subjected to cavity pressure and inviscid oblique shock

On the aeroelastic bifurcation of a flexible panel subjected to cavity pressure and inviscid oblique shock

Nonlinear aeroelastic behavior of a panel impinged by oscillating shock

Fluid structure interactions generated by an oblique shock impinging on a thin elastic panel

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