Unsteady Surface and Flowfield Measurements in Ramp-Induced Turbulent and Transitional Shock-Wave Boundary-Layer Interactions at Mach 6

Whalen, Thomas J.; Kennedy, Richard E.; Laurence, Stuart J.; Sullivan, Bryson T.; Bodony, Daniel J.; Buck, Gregory M.

doi:10.2514/6.2019-1127

Cited by 15 publications

(2 citation statements)

References 21 publications

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“…These modified turbulence statistics were found to converge back to the original rigid panel form within one integral length of the turbulent boundary layer downstream of the panel. Sullivan and Bodony (2019) performed highfidelity two-dimensional laminar unsteady simulations in conjunction with the experiments of Whalen et al (2019) of a M ∞ = 6.04 flow over a 35 • compression ramp with an embedded compliant panel. Several reduced-order models based on piston theory were assessed.…”

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

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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: 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

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“…Sullivan et al[7] used high-fidelity simulations to investigate a 2D compression ramp in Mach 6 flow with a compliant panel imbedded in the ramp. These simulations were conducted in conjunction with complementary experiments carried out by Whalen under the same conditions[8]. Pandey et al[9] conducted similar experiments on a flexible compression ramp at a variety of hypersonic Mach numbers and wedge angles, though the compression ramp in this case was placed on a longitudinally sliced part of a cone, increasing the complexity of the problem.…”

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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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Detection of second-mode instabilities on a flared cone in Mach 6 quiet flow with linear array focused laser differential interferometry

2021

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Unsteady Surface and Flowfield Measurements in Ramp-Induced Turbulent and Transitional Shock-Wave Boundary-Layer Interactions at Mach 6

Cited by 15 publications

References 21 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

Fluid/Structure Interaction of Cantilevered Plate in Supersonic Separated Flow

Detection of second-mode instabilities on a flared cone in Mach 6 quiet flow with linear array focused laser differential interferometry

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