A numerical analysis of the inlet-combustor interaction and flow structure through a scramjet
engine at a flight Mach number M= 6 with parallel injection (Strut with circular inlet) is …

Numerical analysis of the hypersonic combustion and flow structure through a scramjet
engine at a flight Mach 7 with parallel fuel injection at different angles of attack, α=(− 5°), 0° …

Numerical analysis of the supersonic combustion and flow structure through a scramjet
engine at Mach 7 with alternating wedge fuel injection and with three angle of attack (α=− 3° …

In the arena of design of combustion chamber of scramjet engine lots of development are
still going on. A properly designed combustor shall promote sufficient mixing of the fuel and …

A parametric study of combustor inlet configuration for supersonic combustion ramjet
(Scramjet) engine has been conducted by solving two-dimensional full Navier–Stokes …

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 …

Multi-strut injection is an approach to increase the overall performance of Scramjet while
reducing the risk of thermal choking in a supersonic combustor. Hence computational …

Numerical investigation of Scramjet combustor is performed with the help of center lobed
strut to act as a parallel fuel injector. The geometry of the combustor plays a major role to get …

This work presents the numerical analysis of the DLR scramjet combustor for different jet
schemes of the double-nozzle injector, namely the various injection directions, injection …

In this research paper, passive method has been considered to improve the mixing and
combustion efficiency of scramjet combustor. Modified and innovative strut injector designs …