Investigation of Flexible Panel Dynamic Response Induced by Coherent Turbulent Vortical Structures

Zope, Anup; Horner, Colby; Collins, Eric; Bhushan, Shanti; Bhatia, Manav

doi:10.2514/6.2021-0251

Cited by 8 publications

(5 citation statements)

References 42 publications

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“…The peak wall pressure of the rigid STBLI is greater than for the flexible case. The pressure drop over the panel prior to flow separation and the reduction of peak wall pressure compared with the rigid case are also seen in numerical simulations by Zope et al (2021) and Pasquariello et al (2015), and experiments by Gramola et al (2020) and Varigonda and Narayanaswamy (2019). For the flexible panel, the wall pressure peaks farther downstream and rises (induced by the separation shock) farther upstream than in the rigid-wall configuration.…”

Section: Effects Of Panel Flexibility On Wall Pressure Skin Friction ...mentioning

confidence: 56%

“…The use of WMLES enables the simulation to be performed at the same Reynolds number (Re ∞ = 49.4 × 10 6 m −1 ), spanning the full panel width and for the same duration as reported in the experiments, allowing for a more complete characterization of STBLI low-frequency motions and coupling with the flexible panel dynamics. Previous numerical studies of the same experiments were conducted by Pasquariello et al (2015) and Zope, Horner, Collins, Bhushan and Bhatia (2021). The former used wall-resolved LES and a finite-element method hyperelastic Saint-Venant-Kirchoff solid solver that neglected structural damping, with a cut-cell immersed boundary method treatment of the fluid-solid interface.…”

Section: Introductionmentioning

confidence: 99%

“…The simulation ran for a shorter duration, remaining in a transient state. Zope et al (2021) utilized both dynamic hybrid RANS/LES and RANS approaches for the flow solver, also neglecting damping in the solid mechanics solver.…”

Section: Introductionmentioning

confidence: 99%

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Fluid–structural coupling of an impinging shock–turbulent boundary layer interaction at Mach 3 over a flexible panel

Hoy

Bermejo-Moreno²

2022

Flow

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We present high-fidelity numerical simulations of the interaction of an oblique shock impinging on the turbulent boundary layer developed over a rectangular flexible panel, replicating wind tunnel experiments by Daub et al. (AIAA Journal, vol. 54, 2016, pp. 670–678). The incoming free-stream Mach and unit Reynolds numbers are $M_{\infty } = 3$ and $Re_{\infty }=49.4\times 10^6 {\rm m}^{-1}$ , respectively. The reference boundary layer thickness upstream of the interaction with the shock is $\delta _0 = 4$ mm. The oblique shock is generated with a rotating wedge initially parallel to the flow that increases the deflection angle up to $\theta _{{max}} = 17.5^{\circ }$ within approximately $15$ ms. A loosely coupled partitioned flow–structure interaction simulation methodology is used, combining a finite-volume flow solver of the compressible wall-modelled large-eddy simulation equations, an isoparametric finite-element solid mechanics solver and a spring-system-based mesh deformation solver. Simulations are conducted with rigid and flexible panels, and the results compared to elucidate the effects of panel flexibility on the interaction. Three-dimensional effects are evaluated by conducting simulations with both full ( $50 \delta _0$ ) and reduced ( $5\delta _0$ ) spanwise panel width, the latter enforcing spanwise periodicity. Panel flexibility is found to increase the separation bubble size and modify its spectral dynamics. Time- and spanwise-averaged streamwise profiles of the wall pressure exhibit a drop over the flexible panel prior to the interaction and a reduced peak pressure in comparison with the rigid case. Spectral analyses of wall pressure data indicate that the low-frequency motions have a similar spectral distribution for the rigid and flexible cases, but the flexible case shows a wider region dominated by low-frequency motions and traces of the panel vibration on the wall pressure signal. The sensitivity of the interaction to small variations in the wedge extent and incoming boundary layer thickness is evaluated. Predictions obtained from lower-fidelity modelling simplifications are also assessed.

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Section: Effects Of Panel Flexibility On Wall Pressure Skin Friction ...mentioning

confidence: 56%

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Fluid–structural coupling of an impinging shock–turbulent boundary layer interaction at Mach 3 over a flexible panel

Hoy

Bermejo-Moreno²

2022

Flow

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“…Shinde et al [21] investigated the shock wave turbulent boundary layer interaction over a flexible panel by performing large eddy simulations (LES) with fluid-structure coupling method, and modal analysis were carried out to identify the coupling between system components. Zope et al [22] studied dynamics of the oblique shock wave and turbulent boundary layer with a flexible panel by using hybrid Reynolds averaged Navier-Stokes/large eddy simulation (RANS/LES) methods and compared the predictive capabilities of low-fidelity and high-fidelity turbulence modelling approaches.…”

Section: Introductionmentioning

confidence: 99%

“…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%

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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Numerical study of the effect of micro vortices on chaotic flutter

Palakurthy

Zope

Yan

et al. 2024

Journal of Computational and Applied Mathematics

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Investigation of Flexible Panel Dynamic Response Induced by Coherent Turbulent Vortical Structures

Cited by 8 publications

References 42 publications

Fluid–structural coupling of an impinging shock–turbulent boundary layer interaction at Mach 3 over a flexible panel

Fluid–structural coupling of an impinging shock–turbulent boundary layer interaction at Mach 3 over a flexible panel

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

Numerical study of the effect of micro vortices on chaotic flutter

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