Simultaneous pressure and displacement measurements on a 3D flexible surface in a supersonic flow

Ravichandran, Raghul; Gramola, Michela; Bruce, Paul J.

doi:10.2514/6.2020-0315

Cited by 4 publications

(2 citation statements)

References 8 publications

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“…Casper et al [2], for example, studied the effects of intermittent turbulent spots on the dynamic response of a compliant panel embedded in a slender cone in hypersonic flow. Ravichandran et al [3] controlled the cavity pressure behind their flexible panel geometry to investigate the influence of cavity pressure on the motion of the panel. Ravichandran et al [3] also investigated the response of their panel to impingement by an oblique shock wave, another common focus of FSI research that uses the unsteady interaction of the shock wave with the boundary layer as a forcing mechanism for the flexible panel rather than a turbulent boundary layer.…”

Section: Acknowledgmentsmentioning

confidence: 99%

Fluid/Structure Interaction of Cantilevered Plate in Supersonic Separated Flow

2022

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The fluid-structure interaction of a cantilevered plate geometry in Mach 2 flow was studied experimentally to assess the effects of structural compliance on the surrounding flowfield. The test geometry, representative of a compliant control surface, consists of an overhanging plate that extends past the edge of a backward-facing step to create a separated region in the flow. This allowed for the study of recirculation effects and unsteady pressure forcing on the cantilevered plate without shock/boundary-layer interactions that would be present if the plate were inclined to the flow. Rigid and compliant test articles were studied to capture the fluid response with and without structural deformation. Schlieren photography and particle image velocimetry showed that under the unsteady conditions during startup of the wind tunnel the flexible plate exhibited a highly dynamic oscillatory response with frequencies similar to its natural vibration response. Under steady, started supersonic flow conditions, the flexible cantilever exhibited smaller oscillations around a mean deflection of two plate thicknesses. Oil flow visualization revealed nontrivial three-dimensionality of the test section flowfield. Modal decomposition of stereo digital image correlation measurements demonstrated that the distinct frequencies present in the flexible plate’s response consistently correspond to the same mode shapes.

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Section: Acknowledgmentsmentioning

confidence: 99%

Fluid/Structure Interaction of Cantilevered Plate in Supersonic Separated Flow

2022

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“…Recent studies by Ogg et al [28] and Lynch et al [30] demonstrated the use of DIC to successfully capture PSP and surface shape deformation simultaneously for compliant bumps in transonic flow and shock tube testing respectively; however, these studies relied on applying a physical speckle pattern to the model (as a result of using uniform illumination), thereby compromising the PSP. Ravichandran et al [31] and Gramola et al [32] measured similar compliant structures using binary PSP using photogrammetry targets applied after the PSP layer generating a sparse surface mesh. Applying targets in this way has the potential to be aerodynamically intrusive, particularly in sensitive flows such as transonic shockwave boundary layer interactions.…”

Section: Introductionmentioning

confidence: 99%

Simultaneous measurement of surface shape and pressure using structured illumination

Quinn

Fisher

2020

Meas. Sci. Technol.

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This article describes the successful implementation of a structured UV light field, generated from a modified LCD projector, to excite pressure-sensitive paint (PSP) and measure surface shape simultaneously without the need to compromise the PSP by mechanical degradation of the coating. Using commercially available hardware, results were gathered in a Mach 5 wind tunnel, showing the expected pressure distribution around a cone model with a flare and the surface geometry without any prior knowledge or information. The demonstrated methodology can be used to measure aerodynamic models exhibiting elastic deformation under load during a wind tunnel measurement campaign, providing out-of-plane motions are small. The captured deformation and pressure results can be used to support validation of structural models and correct numerical simulation meshes to the actual shape investigated in the wind tunnel.

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