Transonic buffet control research with two types of shock control bump based on RAE2822 airfoil

Tian, Yajie; Gao, Shiqi; Liu, Peiqing; Wang, Jinjun

doi:10.1016/j.cja.2017.07.011

Cited by 30 publications

(33 citation statements)

References 25 publications

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“…As mentioned before, most of the current numerical studies focus on how to achieve the high-precision buffeting response by investigating the sensitivity of simulations to turbulence modelling, spatial and temporal discretization and numerical schemes. The purpose of buffet control is to reduce or even eliminate the unsteadiness of buffet flow as much as possible through appropriate control strategies, thereby reducing the vibration level of the wing [110][111][112][113][114].…”

Section: Type Ii: Instability On the Fluid Mode In The Pre-buffet Flomentioning

confidence: 99%

Transonic aeroelasticity: A new perspective from the fluid mode

Gao

Zhang

2020

Progress in Aerospace Sciences

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Within the transonic regime, the aeroelastic problems exhibit many unique characteristics compared with subsonic and supersonic cases. Although a lot of research has been carried out in this field, the underlying mechanisms of these complex phenomena are not clearly understood yet, resulting in a challenge in the design and use of modern aircraft. This review summarizes the recent investigations on nonclassical transonic aeroelastic problems, including transonic buzz, reduction of transonic buffet onset, transonic buffeting response and frequency lock-in phenomenon in transonic buffet flow. After introducing the research methods in unsteady aerodynamics and aeroelastic problems, the dynamical characteristics as well as the physical mechanisms of these phenomena are discussed from the perspective of the fluid mode. In the framework of the ROM (reduced order model) -based model, the dominant fluid mode (or the eigenvalue) and its coupling process with the structural model can be clearly captured. The flow nonlinearity was believed to be the cause of the complexity of transonic aeroelasticity. In fact, this review indicates that the complexity lies in the decrease of the flow stability in the transonic regime. In this condition, the fluid mode becomes a principal part of the coupling process, which results in the instability of the fluid mode itself or the structural mode, and thus, it is the root cause of different transonic aeroelastic phenomena.

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Section: Type Ii: Instability On the Fluid Mode In The Pre-buffet Flomentioning

confidence: 99%

Transonic aeroelasticity: A new perspective from the fluid mode

Gao

Zhang

2020

Progress in Aerospace Sciences

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“…As such, most of the following work in SCBs for buffet control tended towards more wedge-based geometric configurations. More recently, a study by Tian et al [24] investigated the performance of a simple hill-type SCB on buffet suppression on the RAE2822 aerofoil at two positions along the rear of the aerofoil. These findings showed that whilst both bumps were capable of mitigating buffet at the design point, the rearward positioned bump provided only a marginal shift in buffet onset.…”

Section: Overview Of Shock Control Bumps In Transonic Flowsmentioning

confidence: 99%

“…Further, the choice of SCB position is made more complex due to the oscillatory nature of the shock within this region. The SCBs investigated by Tian et al [24] strictly compared two positions aft of the mean shock location with fixed lengths and marginal difference in SCB heights. The work from Geoghegan et al [31] showed that the range of applicable geometries for buffet suppression is potentially much larger than the limited scope for drag reduction, which is the case for stationary shock systems.…”

Section: Overview Of Shock Control Bumps In Transonic Flowsmentioning

confidence: 99%

“…Table 1 contains a summary of the four test cases where individual parameters were varied. These values were based on the ranges cited in a review paper by Bruce [50] on general SCBs, the geometries evaluated by Tian et al [24,51], and those from Geoghegan et al [31]. Table 1.…”

Section: Influence Of Scb Parameters On Shock Control and Flow Responsementioning

confidence: 99%

“…Contour-bumps, alternatively, are usually described by a smooth, continuous surface deformation (relative to wedge-bumps). The efficacy of these geometries is still contested in terms of their performance in drag reduction in pre-buffet conditions; however, both approaches seem to offer either alleviation in 2D/3D [22,23] or complete suppression in 2D [24] in on-design conditions. Given that these devices inherently must be designed for a particular flight condition for optimal performance, the impact of a fixed SCB on a wing can often lead to diminished off-design performance relative to the clean wing configuration.…”

Section: Introductionmentioning

confidence: 99%

See 2 more Smart Citations

A Numerical Investigation of the Geometric Parametrisation of Shock Control Bumps for Transonic Shock Oscillation Control

Geoghegan

Giannelis

Vio

2020

Fluids

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At transonic flight conditions, shock oscillations on wing surfaces are known to occur and result in degraded aerodynamic performance and handling qualities. This is a purely flow-driven phenomenon, known as transonic buffet, that causes limit cycle oscillations and may present itself within the operational flight envelope. Hence, there is significant research interest in the development of shock control techniques to either stabilise the unsteady flow or raise the boundary onset. This paper explores the efficacy of dynamically activated contour-based shock control bumps within the buffet envelope of the OAT15A aerofoil on transonic flow control numerically through unsteady Reynolds-averaged Navier–Stokes modelling. A parametric evaluation of the geometric variables that define the Hicks–Henne-derived shock control bump will show that bumps of this type lead to a large design space of applicable shapes for buffet suppression. Assessment of the flow field, local to the deployed shock control bump geometries, reveals that control is achieved through a weakening of the rear shock leg, combined with the formation of dual re-circulatory cells within the separated shear-layer. Within this design space, favourable aerodynamic performance can also be achieved. The off-design performance of two optimal shock control bump configurations is explored over the buffet region for M = 0.73, where the designs demonstrate the ability to suppress shock oscillations deep into the buffet envelope.

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Numerical Analysis of Transonic Buffet Control Using a Two-Dimensional Bump for a Supercritical Aerofoil

Yao

Ogawa

2019

Lecture Notes in Electrical Engineering

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Transonic buffet control research with two types of shock control bump based on RAE2822 airfoil

Cited by 30 publications

References 25 publications

Transonic aeroelasticity: A new perspective from the fluid mode

Transonic aeroelasticity: A new perspective from the fluid mode

A Numerical Investigation of the Geometric Parametrisation of Shock Control Bumps for Transonic Shock Oscillation Control

Numerical Analysis of Transonic Buffet Control Using a Two-Dimensional Bump for a Supercritical Aerofoil

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