An experimental study of the interaction between a glancing shock wave and a turbulent boundary layer

Abstract

The glancing interaction between an oblique shock wave and a turbulent boundary layer has been studied experimentally using a variable-incidence wedge mounted from the side wall of a supersonic wind tunnel. The Mach number was 2·3 and the Reynolds number 5 × 104, based on the 99·5 % thickness of the boundary layer just upstream of the interaction region. The study includes oil flow pictures, vapour and smoke-screen photographs, wall-pressure distributions and local heat-transfer measurements. The results suggest that the complicated interaction region involves two viscous layers: an induced layer formed from fluid initially in the boundary layer growing along the wedge surface near the root, and the thick turbulent layer on the tunnel side wall. The mutual interference between these layers is described, separation is defined and a discussion of incipient separation is included.

Advances in CFD prediction of shock wave turbulent boundary layer interactions

“…For explaining the high heat-transfer peak Advances in CFD Prediction of Shock Wave Turbulent Boundary Layer Interactions measured on the flat plate near the root of the fin, he suggested that a separation conical vortex appears between the separation and the reattachment lines. Kubota and Stollery [146] improved the flow model of Token based on their own experiments. The separated flow in their model is characterized by two counter-rotating vortices -a tight, vigorous, roughly circular one in the corner with a weak, very elongated one above it (Fig.…”

Inception length to a fully developed, fin-generated, shock-wave, boundary-layer interaction

“…This viewpoint was previously stated by Kubota and Stollery for fin interactions. 18 The inception point was determined as follows. A straightline asymptote was fitted to the far-field portion of the upstream-influence line.…”

Investigation of Three-Dimensional Shock Wave/Turbulent-Boundary-Layer Interaction Initiated by a Single Fin

“…This quasi-conical flow A characteristic was later confirmed by many other investigators. [6][7][8][9][10][11][12][13][14] Consequently, a spherical polar coordinate system has been widely used as a proper framework for the analysis of this kind of flows. With the varying of the shock-wave strength (via incoming flow Mach number and fin deflection angle), the flow topology can change significantly.…”