FSI study of 2D adaptive shock control bumps

Gramola, Michela; Bruce, Paul J.; Santer, Matthew

doi:10.2514/6.2019-1845

Cited by 4 publications

(2 citation statements)

References 14 publications

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“…For both concepts the authors performed simulations with coupled fluidstructure interaction (FSI) as well as wind tunnel measurements. Similar simulations using FSI have been performed by Gramola et al [82,83] and Shinde et al [84,85].…”

Section: Thin Flexible Platesupporting

confidence: 65%

Review of Adaptive Shock Control Systems

et al. 2021

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Drag reduction plays a major role in future aircraft design in order to lower emissions in aviation. In transonic flight, the transonic shock induces wave drag and thus increases the overall aircraft drag and hence emissions. In the past decades, shock control has been investigated intensively from an aerodynamic point of view and has proven its efficacy in terms of reducing wave drag. Furthermore, a number of concepts for shock control bumps (SCBs) that can adapt their position and height have been introduced. The implementation of adaptive SCBs requires a trade-off between aerodynamic benefits, system complexity and overall robustness. The challenge is to find a system with low complexity which still generates sufficient aerodynamic improvement to attain an overall system benefit. The objectives of this paper are to summarize adaptive concepts for shock control, and to evaluate and compare them in terms of their advantages and challenges of their system integrity so as to offer a basis for robust comparisons. The investigated concepts include different actuation systems as conventional spoiler actuators, shape memory alloys (SMAs) or pressurized elements. Near-term applications are seen for spoiler actuator concepts while highest controllability is identified for concepts several with smaller actuators such as SMAs.

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Section: Thin Flexible Platesupporting

confidence: 65%

Review of Adaptive Shock Control Systems

et al. 2021

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“…photogrammetry is employed to obtain accurate model deformation data during the experiments. As described in [15] and [16], four Phantom high-speed cameras are placed around the working section, and 80 coded targets, made of white vinyl, are attached to the flexible plate to facilitate the generation of the 3D model using the commercial photogrammetry software photoModeler by EOS Motion [17]. For this setup, the RMS error was calculated to be 30 µm [16], which can be considered negligible for the experiments presented in this paper.…”

Section: Methodsmentioning

confidence: 99%

Off-design performance of 2D adaptive shock control bumps

Gramola

Bruce

Santer

2020

Journal of Fluids and Structures

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Adaptive shock control bumps can exploit the on-design drag-reducing potential of 2D bumps, while mitigating their off-design performance deterioration through geometric modifications. In this study, experiments and simulations have been employed to investigate the wave-drag reducing potential of (actuated and unconstrained) 2D adaptive shock control bumps over a wide range of shock positions. Experiments were carried out in the Imperial College supersonic wind tunnel, modelling the adaptive bump as a flexible surface placed beneath a Mach 1.4 shock wave. 2D RANS CFD simulations of the flow in a parallel channel with a solid bump complement experiments. Wave drag was demonstrated to be proportional to the ratio of inlet to exit stagnation pressure in a blow-down wind tunnel for a given shock position. The shock exhibits a hysteretic behaviour when travelling in the wind tunnel working section, governed by the wave drag reducing potential of the bump. The actuated adaptive bump tested reduces wave drag over a wider operational envelope than solid bumps as experiments revealed the presence of three preferred structural configurations, which lead to a significantly enlarged hysteresis region. Finally, tests on unconstrained bumps were shown to increase wave drag, both on-and off-design, due to the unfavourable bump shapes that result from (only) passive actuation, suggesting that some constraints are required to achieve desirable surface deformations.

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Oblique Shock Control with Steady Flexible Panels

2020

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Flexible panels deforming under pressure loads have been suggested as a passive form of adaptive oblique shock control. This study investigates oblique shock-boundary layer interactions on a steady flexible panel in a Mach 2.0 flow. Experiments were performed in the Imperial College supersonic wind tunnel, where shock generators were used to produce an oblique shock followed by a corner expansion. A parametric study was conducted, exploring different shock impingement positions and shock-expansion distances. The steady aero-structural response is studied using schlieren photography, static pressure distributions, photogrammetry measurements, and surface oil flow visualisation. Two-dimensional numerical simulations were

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FSI study of 2D adaptive shock control bumps

Cited by 4 publications

References 14 publications

Review of Adaptive Shock Control Systems

Review of Adaptive Shock Control Systems

Off-design performance of 2D adaptive shock control bumps

Oblique Shock Control with Steady Flexible Panels

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