Numerical Study of Transonic Buffet on a Supercritical Airfoil

Xiao, Qing; Tsai, Her Mann; Liu, Feng

doi:10.2514/1.16658

Cited by 90 publications

(28 citation statements)

References 24 publications

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“…Shock movement in such a configuration is known as "the buffeting phenomenon". Recent numerical investigations (Deck, 2005;Xiao and Tsai, 2006) support the theory proposed by Lee (1990) who suggested that the separation (point 2 in figure 6) causes large scale structures that are convected downstream. As these structures reach the trailing edge (point 1 in figure 6) they interact with the flow coming from underneath the airfoil.…”

Section: Comparison With Other Studiessupporting

confidence: 59%

Investigation of large scale shock movement in transonic flow

Wollblad

Davidson

Eriksson

2010

International Journal of Heat and Fluid Flow

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Int. J. of Heat and Fluid Flow, Vol. 31(4), pp. 528-535, 2010 Large eddy simulations were made of transonic flow over a two-dimensional bump where shock wave turbulent boundary layer interaction takes place. Different flow conditions were investigated to find conditions for large scale shock movement. The innermost part of the shock was found to be moving for sufficiently strong shocks. None of the cases display large scale movement of the whole shock.

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Section: Comparison With Other Studiessupporting

confidence: 59%

Investigation of large scale shock movement in transonic flow

Wollblad

Davidson

Eriksson

2010

International Journal of Heat and Fluid Flow

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“…The positive time delays are obtained, indicating that the pressure disturbances within the separated region behind the shock wave propagate downstream towards the aerofoil trailing edge. The local propagation speed of the pressure disturbances can be calculated by dividing the spatial distances between the neighbouring probes by the time delays between the peaks of the corresponding cross-correlations (Xiao et al 2006). Then, the speed is determined as approximately 0.34U ∞ , consistent with the convection speed of the coherent vortical structures, 0.35U ∞ , given above.…”

Section: Pressure Power Spectral Analysis In Turbulent Boundary Layermentioning

confidence: 89%

“…Lee 1990; Xiao, Tsai & Liu 2006), we notice that there exist two typical differences between the present type C and the type A shock wave motion. As a symmetrical aerofoil is considered, unlike only an oscillating shock wave on the upper surface of a supercritical aerofoil (Lee 1990;Xiao et al 2006), the upstreampropagating shock waves occur alternately between the upper and lower surfaces. The period of shock wave motion in this problem is referred to as the complete process of both the shock waves propagating upstream and leaving the aerofoil, as shown in figure 7.…”

Section: Feedback Model Of Shock Wave Motionmentioning

confidence: 99%

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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“…From large eddy simulations to dedicated turbulence models connected to the unsteady Reynolds averaged method [4], [5], [6] there is no generally robust method especially in three dimensions, even if large meshes are to be employed, from 0.2 to 1 billion cells, making the computation expensive, time consuming and requiring experts in the field, which need years of dedicated, sustained work on this specific topic, for which funding is not persistent. It is difficult or impossible in a normal project timeframe to try to align the experimental results with the numerical work, since the current wind tunnel model has laminar areas combined with turbulent contaminated areas due to steps and gaps, as the current model is built, which nearly makes impractical the use of regular CFD methodology.…”

Section: Incas Bulletin Volume 7 Issue 2/ 2015mentioning

confidence: 99%