Abstract
SummaryIn this paper we present the results of the numerical investigation of the shock wave/turbulent boundary layer interaction on a compression corner. The calculations are performed using the Favre-averaged Navier-Stokes equations and a. k — ε turbulence model with compressibility corrections and near-wall modeling. The compressibility terms in the transport equation for the turbulent kinetic energy are based on the Sarkar et al. model [6,7], while the compressibility effects in the equation for the dissipation rate are based on the model of Coleman and Mansour [2]. Flowfield data are presented for a compression corner angle of 24°, with Mach number 2.84, and compared with the experimental data of Settles, Fitzpatrick and Bogdonoff reported in [3]. A good prediction of the upstream influence has been obtained by a careful specification of the incoming boundary layer matching the available experimental informations.
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