Flow performance analysis in scramjet engine inlet for improved diffusion

Abstract

Scramjet inlets are critical to design and have significant effects on the overall performance of the engine. It is necessary to have a precise inlet design for improved performance. The flow is highly supersonic so it produces heavy shock and it requires a design to diffuse from hypersonic Mach number to a speed at which combustion is practically possible say below Mach 4. Further increase in Mach number at inlet will still raise the danger of depleted engine performances. At inlet ramps are usually kept to diffuse the inlet Mach number thereby producing aerodynamic compression. This research work intends to reduce the Mach number using three ramp with various angles and ramp length. By doing this Smooth combustion can be achieved with high level of diffusion without the problems of carryover. A ramp design is made using CATIA and meshed using ICEM CFD and Flow analysis is carried out using Fluent.