NUMERICAL-SIMULATION OF CONFINED TRANSONIC NORMAL SHOCK-WAVE TURBULENT BOUNDARY-LAYER INTERACTIONS

A numerical simulation and experimental investigation of a steady, two -dimensional, Mach 1.48 normal shock wave/turbulent boundary-layer int eraction (NSTBLI) in a diffuser configuration have been conducted. Thi s paper reports the results of the numerical simulation. Compared to p revious investigations, the flow problem is distinguished by the relat ively large ratio of boundary-layer thickness to duct height (0.1) at the beginning of the NSTBLI, and the adverse pressure gradient imposed on the recovering boundary layer by duct divergence. High levels of i nitial blockage change the displacement thickness variation through th e NSTBLI and increase the incipient separation Mach number, whereas th e adverse downstream pressure gradient alters the boundary-layer recov ery following the shock. The motivation for this research is a better understanding of the role of the various parameters influencing the gl obal features of NSTBLIs. Computations of wall static pressure, displa cement thickness, and shape factor distributions and contours of the s treamwise component of velocity and Reynolds stress are compared with experiment.