Supersonic spray combustion is one of the most significant physiochemical processes that
occurs in the scramjet propulsion system, and related research can motivate the …

Kerosene/air two-phase rotating detonation is numerically investigated to find out the limits
of detonation stability as a function of total pressure and total temperature considering the …

The mixing and evaporation process of a liquid kerosene jet in a scramjet combustor with
dual-cavity is investigated by two-phase Large Eddy Simulation. The gas-droplet flow …

Stoichiometric acetylene-oxygen mixtures diluted by argon are widely used in normal
detonation waves but have not yet been used in oblique detonation waves (ODWs). The …

Direct numerical simulation of a spatially developing supersonic mixing layer with a
convective Mach number of 1.0 is conducted. The present work focuses on the structural …

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 …

Mixing and combustion of a fuel with supersonic airstream in a scramjet combustor is a
complex phenomenon because of very less resident time of the air in the combustion …

A numerical study was performed to investigate the detailed effects of activation energy E a
on the oblique detonation wave surface instability. Numerical simulations were performed …

We numerically investigate the mixing and combustion process of a kerosene jet injected
into a scramjet combustor with dual-cavity at different global fuel equivalence ratios using a …

This numerical study investigated the effects of the fresh mixture temperature on
thermoacoustic instabilities in a lean premixed swirl-stabilized combustion chamber by …