Full-field, dynamic pressure and displacement measurements of a panel excited by shock boundary-layer interaction

Spottswood, S. Michael; Eason, Thomas; Beberniss, Timothy J.

doi:10.2514/6.2013-2016

Cited by 58 publications

(14 citation statements)

References 9 publications

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“…The maximum predicted mean displacement during the vibration is about 0.19 mm. The predicted displacement is close to that measured in the experiment [41], which is 0.089 mm. In the simulation of Gogulapati, et al [11], the computed mean displacements for the unheated cases is 0.886 mm, which is substantially more over predicted than the present results.…”

Section: Resultssupporting

confidence: 82%

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Delayed Detached Eddy Simulation of Supersonic Panel Aeroelasticity Using Fully Coupled Fluid Structure Interaction with High Order Schemes

Gan

Zha

2016

34th AIAA Applied Aerodynamics Conference

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This paper conducts delayed detached eddy simulation of a supersonic panel vibration at Mach 2.0. Unsteady 3D compressible Navier-Stokes equations are solved with a system of 5 decoupled structure modal equations in a fully coupled manner. The low diffusion E-CUSP scheme with a 5th order WENO reconstruction for the inviscid flux and a set of 2nd order central differencing for the viscous terms are used to accurately capture the shock wave/turbulent boundary layer interaction of the vibrating panel. The shock waves and their reflection interacting with turbulent boundary layer in the tunnel are well captured by the DDES. The panel vibration induced by the shock boundary layer interaction is well resolved by the simulation. The panel response agrees well with the experiment in terms of the mean panel displacement and frequency. Since it is a fully coupled fluid-structural interaction simulation, the flow and structure responses are captured by the solver itself with no parameter adjustment. The simulation is fairly efficient due to the high order schemes. It takes one week wall clock time to run 0.1s physical time with 264 CPUs using parallel computing.

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Section: Resultssupporting

confidence: 82%

“…The configuration simulated is tested at AFRL Aerospace Systems Directorate large-scale RC-19 supersonic combustion research cell [41], as shown in Fig. 1.…”

Section: Computational Modelmentioning

confidence: 99%

Delayed Detached Eddy Simulation of Supersonic Panel Aeroelasticity Using Fully Coupled Fluid Structure Interaction with High Order Schemes

Gan

Zha

2016

34th AIAA Applied Aerodynamics Conference

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“…Some recent studies that have focused on shock impingements on compliant surfaces are described in [4][5][6][7][9][10][11][12]. Visbal [9,10] investigated the coupled fluid-structural response of a panel for two-dimensional (2-D) Mach 2 flow with an impinging shock.…”

Section: Introductionmentioning

confidence: 99%

“…Results indicated that the panel response was sensitive to dynamic motion of the shock impingement point, and also the back pressure. A current focus of the Air Force Research Laboratory (AFRL) Structural Sciences Center (SSC) is to carry out a series of discovery experiments to investigate the response of thin-gauge panels to shock impingements [4][5][6][7]. The experiments are performed in the AFRL RC-19 supersonic wind tunnel.…”

Section: Introductionmentioning

confidence: 99%

“…However, shock impingements, and the associated response of inflicted panels, are challenging to study since they require high fidelity fluid and structural models to capture both the loads and the structural response accurately. Moreover, experimental study of the fully coupled problem is extremely challenging [4][5][6][7]. Computational modeling of shock-boundary layer interactions remains an open area of research [8], where LES and DNS approaches are required for reasonable predictive accuracy of the fluid dynamics.…”

Section: Introductionmentioning

confidence: 99%

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Response of a Panel to Shock Impingement: Modeling and Comparison with Experiments

Miller

Crowell

Deshmukh

et al. 2014

55th AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference

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A preliminary assessment is developed for long time record modeling and simulation of coupled flow-structural response of thin-gauge panels subject to shock impingements. The study is based on a set of recent discovery experiments carried out by the Air Force Research Laboratory. The fluid loads are modeled using a CFD surrogate for the steady surface pressure combined with engineering level approximations for unsteady pressure fluctuations due to panel vibration and boundary layer turbulence. The structure is modeled using both full-order and reduced-order finite element formulations. Initial comparisons indicate reasonable confidence in modeling the steady component of pressure and structural modeling, and less confidence in modeling the fluctuating pressure and dynamic panel response. Several sources of modeling and measurement uncertainties are highlighted.

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Experiments on Aerothermal Supersonic Fluid-Structure Interaction

Daub

Willems

Esser

et al. 2020

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

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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.

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Full-field, dynamic pressure and displacement measurements of a panel excited by shock boundary-layer interaction

Cited by 58 publications

References 9 publications

Delayed Detached Eddy Simulation of Supersonic Panel Aeroelasticity Using Fully Coupled Fluid Structure Interaction with High Order Schemes

Delayed Detached Eddy Simulation of Supersonic Panel Aeroelasticity Using Fully Coupled Fluid Structure Interaction with High Order Schemes

Response of a Panel to Shock Impingement: Modeling and Comparison with Experiments

Experiments on Aerothermal Supersonic Fluid-Structure Interaction

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