Onset of separation unsteadiness in hypersonic shock boundary layer interaction on a cone-step

TL;DR

This study investigates the unsteady behaviors of shock-boundary layer interactions on a hypersonic cone-step at Mach 6, revealing regime transitions, dominant oscillation modes, and nonlinear shock dynamics through experiments and simulations.

Contribution

It provides a comprehensive analysis of unsteadiness regimes and shock dynamics in hypersonic cone-step flows, combining experimental observations with high-fidelity simulations.

Findings

Regime transition from shear-layer breakdown to pulsations identified.

Dominant oscillation modes characterized by specific Strouhal numbers.

Detailed nonlinear shock dynamics and shear layer instability described.

Abstract

Shock-boundary layer interactions (SBLI) on hypersonic cone step flows exhibit a range of intrinsic unsteady behaviors, from shear-layer oscillations to large-scale pulsations. This work investigates the unsteadiness in a cone-step geometry at Mach 6 under quiet flow conditions at different freestream Reynolds numbers using time-resolved Schlieren imaging and spectral proper orthogonal decomposition (SPOD). Experimental results are compared with high-fidelity axisymmetric and three-dimensional simulations. Results demonstrate regime transition in the parameter space, across the unsteadiness boundary, all the way from shear-layer breakdown to shock system oscillations and ultimately to large-amplitude pulsations. The dominant mode in the experiments and the simulations corresponds to a Strouhal number St ~ 0.17 for small oscillations reducing to St ~ 0.13 for large pulsations. A detailed description of the unsteady shock dynamics, the instability of the shear layer during onset of unsteadiness and an analysis of the nonlinear limit cycle is presented.