Aero-thermo-elastic Simulation of Shock-Boundary Layer Interaction over a Compliant Surface

Shahriar, Al; Shoele, Kourosh; Kumar, Rajan

doi:10.2514/6.2018-3398

Cited by 10 publications

(4 citation statements)

References 30 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…They found self-sustained oscillations of the structure and showed that the dynamic pressure necessary decreases with increasing shock strength. Another recent numerical study on FSI with laminar SWBLI was done by [49]. They observed self-excited oscillations which increased in amplitude with increase of incident shock strength.…”

Section: Fsi and Swblimentioning

confidence: 97%

Experiments on Aerothermal Supersonic Fluid-Structure Interaction

Daub

Willems

Esser

et al. 2020

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

View full text Add to dashboard Cite

Mastering aerothermal fluid-structure interaction (FSI) is crucial for the efficient and reliable design of future (reusable) launch vehicles. However, capabilities in this area are still quite limited. To address this issue, a multidisciplinary experimental and numerical study of such problems was conducted within SFB TRR 40. Our work during the last funding period was focused on studying the effects of moderate and high thermal loads. This paper provides an overview of our experiments on FSI including structural dynamics and thermal effects for configurations in two different flow regimes. The first setup was designed to study the combined effects of thermal and pressure loads. We investigated a range of conditions including shock-wave/boundary-layer interaction (SWBLI) with various incident shock angles leading to, in some cases, large flow separation with high amplitude temperature dependent panel oscillations. The respective aerothermal loads were studied in detail using a rigid reference panel. The second setup allowed us to study the effects of severe heating leading to plastic deformation of the structure. We obtained severe localized heating resulting in partly plastic deformations of more than 12 times the panel thickness. Furthermore, the effects of repeated load cycles were studied.

show abstract

Section: Fsi and Swblimentioning

confidence: 97%

Experiments on Aerothermal Supersonic Fluid-Structure Interaction

Daub

Willems

Esser

et al. 2020

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

View full text Add to dashboard Cite

show abstract

“…The boundary conditions for the leading and trailing edges are specified as pinned. The final discretized structural dynamic equations can be written in the following form of (11) where   M denotes the mass matrix,   C denotes the damping matrix,   K denotes the stiffness matrix, and F denotes the loads vector. u is the structural deformation vector.…”

Section: Structure Modelingmentioning

confidence: 99%

“…In addition, the laminar cases [10] showed the coupling of boundary layer instabilities with higher-order structure modes, and complex non-periodic self-excited oscillations of multiple higher frequencies were observed. Shahriar et al [11] also studied the shock wave laminar boundary layer interaction over a compliant surface, and effects of different thermal boundary conditions were investigated. Building on Visbal's work [9], Boyer et al [12] examined the features of shock-induced panel flutter in three-dimensional inviscid flow and found very similar dynamic characteristics near the centerline.…”

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

View full text Add to dashboard Cite

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.

show abstract

“…To predict aerodynamic forces acting on a deforming structure, simplified formulations based on piston, Van Dyke and shock-expansion theories are common for quasi-steady interactions, due to the minimal computational cost (Brouwer & McNamara, 2019;McNamara & Friedmann, 2007;. For higher physical fidelity, prior studies have resorted to solving the inviscid Euler flow equations (Visbal, 2012) or the Navier-Stokes equations via Reynolds-averaged Navier-Stokes (RANS) approaches (Gogulapati et al, 2014;Shahriar, Shoele, & Kumar, 2018;Visbal, 2014;Yao, Zhang, & Liu, 2017), detached-eddy simulations (Gan & Zha, 2016), large-eddy simulation (LES) (Borazjani & Akbarzadeh, 2020;Pasquariello et al, 2015) or direct numerical simulation (Shinde, McNamara, Gaitonde, Barnes & Visbal, 2018), coupled with structural solvers (Schemmel, Collins, Bhushan, & Bhatia, 2020). Although attractive from a computational cost standpoint, RANS approaches cannot accurately predict strong flow separation and associated low-frequency dynamics in STBLIs (Sadagopan, Huang, Xu, & Yang, 2021).…”

Section: Introductionmentioning

confidence: 99%

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

Hoy

Bermejo-Moreno²

2022

Flow

View full text Add to dashboard Cite

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.

show abstract

Aero-thermo-elastic Simulation of Shock-Boundary Layer Interaction over a Compliant Surface

Cited by 10 publications

References 30 publications

Experiments on Aerothermal Supersonic Fluid-Structure Interaction

Experiments on Aerothermal Supersonic Fluid-Structure Interaction

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

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

Contact Info

Product

Resources

About