Partially or completely reusing launch vehicles significantly reduces expenses for
manufacturing and testing in space missions. Thus, Reusable Launch Vehicles (RLV) can …

This paper numerically investigated the dynamic characteristics of combustion in a model
scramjet. Three-dimensional compressible large eddy simulation was performed on a …

Two hypermixer fuel-injector struts, which can induce streamwise vortices in the middle of a
combustor, are used to investigate numerically how the difference of vortex circulation …

In this study, large eddy simulation (LES) has been used to examine supersonic flow,
mixing, self-ignition and combustion in a model scramjet combustor and has been compared …

A supersonic combustion ramjet engine is an air‐breathing propulsive system aimed at
futuristic hypersonic vehicles. The profound advantages observed in the area of defence …

This study describes combustion features due to streamwise vorticity when using hypermixer
struts at Mach numbers of 2.5 and 3.5. Two types of struts are used with hydrogen fuel (at an …

The Multiple Map** Conditioning/Large Eddy Simulation (MMC-LES) model is extended
for the first time to high-speed, compressible flow conditions and validated against non …

Flame stabilization mechanisms of a hydrogen-fueled laboratory model scramjet combustor
are numerically studied. The combustor consists of a sonic fuel jet injected paralleling into a …

To investigate the potential performance benefits of tailored fuel injection in a scramjet
engine, flow through a rectangular-to-elliptical shape-transitioning scramjet was simulated …

This paper presents a numerical simulation study of the combustion structure of streamwise
vortex breakdown at Mach number 2.48. Hydrogen fuel is injected into a combustor at sonic …