Effect of Divergence Angles on the Performance of a Cavity-Based Scramjet Combustor

Supersonic combustion is a work-in-progress field primarily dealing with difficulties in mixing fuel with the free stream air coming into the engine leading to difficulties of inefficient combustion and thus inefficient thrust production. Such new generation engines require unique fluid mechanisms to achieve good mixing. One such approach is changing the shape of the space surrounding the fuel injector yields generates vortices that aids in mixing fuel with air by increasing the residence time of the combustible mixture. In addition to the bespoke shape of the cavity, a diverging cross-sectional area is provided to reduce if not prevent thermal choking. It was found that the trapezoidal shape cavity provided the best metrics with diverging angles.