Description

In this project, a Hypersonic Combustion in Scramjet with Viscous Heating has been simulated, and the simulation results have been investigated using ANSYS Fluent software. We perform this CFD project and investigate it by CFD analysis.

The 2-D geometry of the present model is carried out using Design Modeler software. The geometry consists two-section, the lower section is preheating, and the upper section is a stable burn region.

The meshing of this present model has been generated by Ansys Meshing software. The mesh grid is Structured, and the total cell number is 16320.

Also, due to the nature of the present problem, the transient solver has been enabled.

Hypersonic Combustion in Scramjet Methodology

Scramjets are a type of ramjets that can travel at hypersonic speed while there is no motion device in its engine. Scramjet technology started from the development of the ramjet.

The ramjets might not achieve supersonic speed, while scramjets fly at hypersonic speed. Supersonic speed means the Mach number of more than 1, while hypersonic represents more than 5.

In this project, Hypersonic Combustion in a scramjet engine is simulated. The Mach number of inlet air is set to 6, and the temperature of the whole domain equals 300k.

At the middle part of the nozzle, in which the Mach number reaches 1, hydrogen injects into the flow with a Mach number of more than 1, and consequently, the combustion will occur in the nozzle.

The species transport model and the volumetric sub-model are enabled to model the combustion process. The air is considered an ideal gas to change the density during combustion.

First-order accuracy is chosen for parameters to reach a suitable convergence, and relaxation factors are set at a lower value than the default amount in Ansys Fluent software. Moreover, the standard k-epsilon model is used to solve turbulent fluid equations.

Hypersonic Combustion in Scramjet Conclusion

At the end of the solution process, two-dimensional contours and vectors of flow pressure, temperature, velocity, Mach number, density, and turbulence intensity are obtained.

At first, airflow enters the domain through the inlet face and moves to the combustion portion while the speed decreases to Mach number 1. Then advances to the outlet at a higher speed.

Due to combustion, the amount of temperature passes 4000 K. Also, the effect of viscous heating is visible in elements near the wall.