Numerical simulations of axisymmetric aft wall angle cavity in supersonic combustion ramjets

Scramjet engines are the most favourable candidates for future air breathing propulsive system and are a promising option for high-speed flights. In scramjet engines, air-fuel mixing, flame stabilization and combustion efficiency are still a challenge. Understanding of the phenomena occurring inside the supersonic combustion chamber is therefore mandatory: that is why numerical simulations may be of help toward future SCRJ combustor design. The purpose of this paper is to investigate benefits of axisymmetric cavity with varying aft wall angle. In fact, an optimized cavity is a promising solution to stabilize the flame in supersonic flows avoiding prohibitive total pressure losses, since this enable the generation of a recirculation zone in the cavity, where the flame anchors. The objective of this paper is to numerically examine the impact of diverse toward the back-divider points on blending, pressure losses and combustion efficiency. 3D RANS simulations have been performed and compared with cold stream test data. The result of this study is calculated based on static pressure and stagnation pressure losses. The validation of results with available experimental data shows good agreement. Results shows that cavities with different toward the back-divider points diminish the total pressure loss and move forward blending capabilities by making distribution zones.