Self-sustained shock oscillations on airfoils at transonic speeds

Lee, B.H.K.

doi:10.1016/s0376-0421(01)00003-3

Cited by 346 publications

(143 citation statements)

References 56 publications

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“…To determine the frequency of shock wave motion, figure 8 shows the power spectrum of the time-dependent lift force exerted on the aerofoil. The primary frequency corresponding to the highest peak is St = 0.148 approximately, or the reduced frequency, which is usually used in this problem (Tijdeman & Seebass 1980;Lee 2001), k = πSt ≈ 0.465, consistent with the previous experimental data, namely 0.44-0.49 (e.g. McDevitt et al 1976;Levy 1978;Marvin et al 1980).…”

Section: Shock Wave Motionsupporting

confidence: 87%

Numerical investigation of the compressible flow past an aerofoil

Chen

2009

J. Fluid Mech.

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Numerical investigation of the compressible flow past an 18% thick circular-arc aerofoil was carried out using detached-eddy simulation for a free-stream Mach number M∞ = 0.76 and a Reynolds number Re = 1.1 × 107. Results have been validated carefully against experimental data. Various fundamental mechanisms dictating the intricate flow phenomena, including moving shock wave behaviours, turbulent boundary layer characteristics, kinematics of coherent structures and dynamical processes in flow evolution, have been studied systematically. A feedback model is developed to predict the self-sustained shock wave motions repeated alternately along the upper and lower surfaces of the aerofoil, which is a key issue associated with the complex flow phenomena. Based on the moving shock wave characteristics, three typical flow regimes are classified as attached boundary layer, moving shock wave/turbulent boundary layer interaction and intermittent boundary layer separation. The turbulent statistical quantities have been analysed in detail, and different behaviours are found in the three flow regimes. Some quantities, e.g. pressure-dilatation correlation and dilatational dissipation, have exhibited that the compressibility effect is enhanced because of the shock wave/boundary layer interaction. Further, the kinematics of coherent vortical structures and the dynamical processes in flow evolution are analysed. The speed of downstream-propagating pressure waves in the separated boundary layer is consistent with the convection speed of the coherent vortical structures. The multi-layer structures of the separated shear layer and the moving shock wave are reasonably captured using the instantaneous Lamb vector divergence and curl, and the underlying dynamical processes are clarified. In addition, the proper orthogonal decomposition analysis of the fluctuating pressure field illustrates that the dominated modes are associated with the moving shock waves and the separated shear layers in the trailing-edge region. The results obtained in this study provide physical insight into the understanding of the mechanisms relevant to this complex flow.

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Section: Shock Wave Motionsupporting

confidence: 87%

Numerical investigation of the compressible flow past an aerofoil

Chen

2009

J. Fluid Mech.

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“…An extensively set of data for the buffeting problem studied at the National Research Council, Canada of the flow over the BauerGarabedian-Korn (BGK) No. 1 supercritical airfoil at transonic speed has been reported by Lee 9 , Lee, et al 10 , Lee 11,12 , and Lee, et al 13 . The experiments were conducted over a range of Mach number and angle of attack.…”

Section: Introductionmentioning

confidence: 87%

“…In the present work we employ the lag model coupled with the two-equation k-ω model for the study of transonic buffeting flow for the BGK No.1 supercritical airfoil, which is well documented in the paper of Lee 9 , Lee, et al 10 , and Lee 11,12 .…”

Section: Introductionmentioning

confidence: 99%

Numerical Study of Transonic Buffet on a Supercritical Airfoil

Xiao¹,

Tsai

Liu

2006

AIAA Journal

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“…6 Results from: a Milholen and Owens [13]; b Eastwood and Jarrett [10], reproduced with permission from Jeremy Eastwood also promote boundary layer separation [26]. Despite this, some studies have argued that 2-D SCBs can still have a positive impact on off-design performance in one of the two ways: (1) Delaying the onset of transonic buffet by breaking up large regions of separated flow and inhibiting communication between an oscillating shock and an aerofoil's trailing edge [2,4,18]; and, (2) In the case of a straight ramp-type design, improving shock stability by effectively anchoring the front shock leg [17].…”

Section: -D Scbmentioning

confidence: 99%

Review of research into shock control bumps

Bruce

Colliss

2014

Shock Waves

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This paper presents a review of research on shock control bumps (SCBs), a class of flow control device with potential for application to transonic wings. Beginning with a brief review of the origins of the SCB concept, the primary focus is on the more recent studies from the last decade. Results from both experimental and numerical work are considered and the synergy between these two approaches to SCB research is critically explored. It is shown that the aerodynamic performance enhancement potential of SCBs, namely their capacity for drag reduction and delaying the onset of buffet for transonic wings, has been widely demonstrated in the literature, as has the high sensitivity of SCB performance to flow conditions including shock strength and position, and post-shock adverse pressure gradient. These characteristic features of SCBs are relatively well explained in terms of the flow physics that have been observed for different bump geometries. This stems from a number of studies that have focused on the balance of viscous and inviscid flow features and also the mechanism by which finite span SCBs generate streamwise vorticity. It is concluded that our understanding of SCBs is reaching an advanced level of maturity for SCBs in simple configurations and steady flow fields. However, SCB performance in unsteady flow and on swept wings requires further investigation before the concept can be considered a viable candidate for transonic wings. These investigations should adopt a multi-disciplinary approach combining carefully designed experiments and targeted computations. Finally, two concepts for future SCB research are suggested: the adaptive SCB and SCBs in engine intakes.Communicated by A. Hadjadj.

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Self-sustained shock oscillations on airfoils at transonic speeds

Cited by 346 publications

References 56 publications

Numerical investigation of the compressible flow past an aerofoil

Numerical investigation of the compressible flow past an aerofoil

Numerical Study of Transonic Buffet on a Supercritical Airfoil

Review of research into shock control bumps

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