NUMERICAL INVESTIGATION OF A COMPLETE SCRAMJET MODEL WITH CENTRAL STRUT INJECTION

摘要

A complete scramjet demonstrator model is investigated numerically for flight conditions with and without combustion. The main point of the paper is the design of the combustor, which has to enable a stable and reliable combustion. The incoming air is compressed by a 3D intake causing a strongly three-dimensional and non-homogeneous flow field at the combustor entrance. To avoid blockage and to ensure a good mixing and a stable combustion, a lobed strut injector and ignition wedges are used and assessed. The nozzle design is varied and the respective thrust generation is evaluated. The shock wave system in the combustor, mixing, autoignition, flame stabilization, and fuel burnout are analyzed in the paper. In this way, a design is found that provides a stable supersonic flame with high mixing and combustion efficiencies.