• Corpus ID: 244729195

Oblique transition in hypersonic double-wedge flow: An input-output viewpoint

  title={Oblique transition in hypersonic double-wedge flow: An input-output viewpoint},
  author={Anubhav Dwivedi and G. S. Sidharth and Mihailo R. Jovanovi'c},
We utilize input-output and weakly nonlinear analyses in combination with direct numerical simulations (DNS) to identify mechanisms for oblique transition in a Mach 5 hypersonic flow over an adiabatic slender double-wedge. Even though the laminar separated flow is globally stable, input-output analysis demonstrates significant amplification of unsteady external disturbances. These disturbances are introduced upstream of the separation zone and they lead to the appearance of oblique waves… 


Oblique-mode breakdown and secondary instability in supersonic boundary layers
Laminar–turbulent transition mechanisms for a supersonic boundary layer are examined by numerically solving the governing partial differential equations. It is shown that the dominant mechanism for
Optimal spatial growth of streaks in oblique shock/boundary layer interaction
Direct numerical simulation (DNS) of oblique shock interacting with an incoming laminar boundary layer on an adiabatic flat plate at Mach 5.92 is considered. Various shock angles are considered to
Simulation and stability analysis of oblique shock wave/boundary layer interactions at Mach 5.92
We investigate flow instability created by an oblique shock wave impinging on a Mach 5.92 laminar boundary layer at a transitional Reynolds number. The adverse pressure gradient of the oblique shock
Direct numerical simulation of complete transition to turbulence via oblique breakdown at Mach 3
A pair of oblique waves at low amplitudes is introduced in a supersonic flat-plate boundary layer at Mach 3. Its downstream development and the concomitant process of laminar to turbulent transition
Nonlinear transition mechanism on a blunt cone at Mach 6: oblique breakdown
Abstract Direct numerical simulations (DNS) were carried out to investigate laminar-turbulent transition for a blunt (right) cone ($7^\circ$ half-angle) at Mach 5.9 and zero angle of attack. First,
The objective of this review is to critically assess the different approaches developed in recent years to understand the dynamics of open flows such as mixing layers, jets, wakes, separation
Unsteady effects in a hypersonic compression ramp flow with laminar separation
Abstract Direct numerical simulations (DNS) are performed to investigate a hypersonic flow over a compression ramp with a free stream Mach number of 7.7 and a free stream Reynolds number of
Numerical and experimental investigations of oblique boundary layer transition
A transition scenario initiated by two oblique waves is studied in an incompressible boundary layer. Hot-wire measurements and flow visualizations from the first boundary layer experiment on this
Modeling mode interactions in boundary layer flows via the parabolized Floquet equations
In this paper, we develop a model based on successive linearization to study interactions between different modes in boundary layer flows. Our method consists of two steps. First, we augment the
Input-output analysis of high-speed axisymmetric isothermal jet noise
We use input-output analysis to predict and understand the aeroacoustics of high-speed isothermal turbulent jets. We consider axisymmetric linear perturbations about Reynolds-averaged Navier-Stokes