The structure and the frequency spectra of wall pressure fluctuations beneath a planar
turbulent boundary layer interacting with a conical shock wave at Mach number dB), with an …

To better understand the high temperature non-equilibrium effects of a high Mach number
(above Mach 8) scramjet inlet, the thermal and chemical non-equilibrium flow of Mach 12 …

Supersonic flow over a hollow cylinder/flare with a free-stream Mach number of 2.25 is
numerically investigated in this study. Axisymmetric computational fluid dynamics …

The second moment correlations between thermodynamic fluctuations in incident shock
wave/turbulent boundary layer interaction flows at Mach 2.25 are systematically investigated …

The present numerical investigation focuses on the leading-edge bluntness effects on the
double wedge with varied aft-wedge angles exposed to low enthalpy hypersonic free stream …

We discuss a relationship between wave-packets and discontinuities encountered in the
numerical solution of unsteady, supersonic triple-deck equations. Large gradients at the …

We consider high Reynolds number supersonic flow over a compression ramp in the triple-
deck formulation. Previous studies of compression-ramp stability have shown rapid growth …

The problem of axisymmetric supersonic laminar flow separation over a compression corner
has not been considered within the framework of triple-deck theory for several decades …

The wall temperature of the high-speed aircraft increases quickly under
hypersonic/supersonic incoming flow, which will cause a significant change in the flow …

This study is an attempt at solving steady-state triple-deck equations using the method of
Bos & Ruban (Phil. Trans. R. Soc. Lond. A, vol. 358, issue 1777, 2000, pp. 3063–3073) for …