The interaction of an oblique shock wave with a laminar boundary layer revisited. An experimental and numerical study

Abstract

An investigation of an oblique shock wave/laminar boundary layer interaction is presented. The Mach number was 2.15, the Reynolds number was 105 and the overall pressure ratio was 1.55. The interation has been demonstrated to be laminar and nominally two-dimensional. Experimental results include pressure distributions on the plate and single component laser-Doppler velocimetry velocity measurements both in the attached and separated regions.The numerical results have been obtained by solving the full compressible Navier-Stokes equations with the implicit approximate factorization algorithm by Beam & Warming (1980). Comparison with experimental data shows good agreement in terms of pressure distributions, positions of separation and reattachment and velocity profiles.

Bifurcations in shock-wave/laminar-boundary-layer interaction: global instability approach

“…The test case considered has been experimentally and numerically studied by Degrez et al (1987). The free-stream inflow Mach number is 2.15 for the numerical simulation.…”

“…More precisely, this paper shows that some unsteadiness, in particular the low frequency unsteadiness, originate in a supercritical Hopf bifurcation related to the dynamics of the separated boundary layer. Various direct numerical simulations were carried out of a shock-wave/laminar boundary-layer interaction (SWBLI), resulting from the test case studied by Degrez et al (1987). Three-dimensional unsteady Navier-Stokes equations are numerically solved with an implicit dual time stepping for the temporal algorithm and high order AUSMPW+ scheme for the spatial discretization.…”

Choice of implicit and explicit operators for the upwind differencing method

“…Finally, the Navier-Stokes calculation concerns the interaction of an oblique shock wave with a laminar boundary layer; the flow parameters are those of recent experiments [20] and are given later, along with details about the computational grid used.…”

PNS algorithm for solving supersonic flows with upstream influences

“…In addition to the numerical results, experimental data were obtained from the literature, Refs. [54][55][56][57][58][59][60], and these residts are presented in Tables A.2 The preceding results indicate that the upstream influence associated with ramp flowfields is different from that of shock impingement flowfields. This is due in part to the fact that the boundary layer induces a small turning angle which produces an effective increase in pressure change for shock impingement flowfields and an effective decrease in pressure change for ramp flowfields.…”