INCA

Large-eddy simulation of supersonic turbulent boundary layer over a compression-expansion ramp

M. Grilli, S. Hickel, N.A. Adams (2013)
International Journal of Heat and Fluid Flow 42: 79-93. doi: 10.1016/j.ijheatfluidflow.2012.12.006

Results of a large-eddy simulation (LES) of a supersonic turbulent boundary layer flow along a compression–expansion ramp configuration are presented. The numerical simulation is directly compared with an available experiment at the same flow conditions. The compression–expansion ramp has a deflection angle of β = 25°, the free-stream Mach number is Ma∞ = 2.88, and the Reynolds number based on the incoming boundary layer thickness is Reδ = 132 840.

The Navier Stokes equations for compressible flows are solved on a cartesian collocated grid. About 32.5 × 106 grid points are used to discretize the computational domain. Subgrid scale effects are modeled implicitly by the adaptive local deconvolution method (ALDM). A synthetic inflow-turbulence technique is used, which does not introduce any low frequency into the domain, therefore avoiding any possible interference with the shock/boundary layer interaction system. Statistical samples are gathered over 800 characteristic time scales δ0/U∞. The numerical data are in good agreement with the experiment in terms of mean surface-pressure distribution, skin-friction, mean velocity profiles, velocity and density fluctuations. For the first time the full compression–expansion ramp configuration was taken into account. The computational results confirm theoretical and experimental findings on fluctuation-amplification across the shockwave/boundary layer interaction region and on turbulence damping through the interaction with rarefaction waves. The LES provide evidence of the existence of Görtler-like structures originating from the recirculation region and traveling downstream along the ramp. An analysis of the wall pressure field clearly shows the presence of a low frequency motion of the shock and strong influence of the Görtler-like vortices on the wall pressure spectra.

 

Instantaneous representation of the flow by the Schlieren-type visualization: (a) spanwise averaged density gradient magnitude for the LES and (b) experimental visualization.
Instantaneous snapshot of velocity fluctuation at y+ = 12. The symbols S and R indicate mean separation and reattachment line. Black solid lines indicate compression corner and decompression (expansion) corner of the ramp geometry.

 

Contours of the weighted power spectral density of wall-pressure. The spectra are normalized such that their integral over frequency is unity. Thirty contours levels have been used; the dashed vertical line indicates the location of the separation (S) and reattachment (R) lines. The solid lines indicate the location of the compression (CC) and decompression (DC) corner.

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