Cfd And Thermal Investigation Of A Hypersonic Scramjet Engine Using Various Ramp Angles

Abstract

A scramjet engine is a supersonic combustion ramjet engine which doesn’t have moving parts in the engine. The major differences between ramjet and scramjet engine is flow of air in the combustion chamber. Hypersonic Scramjet engines generally starts at free stream Mach number of 5 to 6 is released from turbojet engines or rockets.

Hypersonic Scramjet engines generally starts at free stream Mach number of 5 to 6 is released from turbojet engines or rockets. Although the scramjet starting with Mach no 4.0 is possible with today’s technology, initially in this project we are going to analyses directly on the supersonic flight to get the velocity of the air passing through it and then later the CFD analysis is carried out at different ramp angles with a starting Mach number of 4.00 and the variation is compared. The model is designed using ANSYS Design Modeler, meshing is done using ANSYS Mesh and CFD analysis is done using ANSYS Fluent. The different contours of the model like pressure, velocity and density contours are plotted. This paper shows the CFD analysis of scramjet inlet at different ramp angles at 20.5⁰, 22.5⁰ and 24.5⁰. Finally the thermal analysis is carried out on the 3d model of the three different angles to find out the flux distribution.