Aerothermodynamic of Supersonic Combustion Processes in Shock-Induced, High Enthalpy Flows

Hypersonic propulsion systems have to deal with extreme flow conditions like strong shock waves and very high temperatures, leading to high enthalpy flows. This flow also have chemical reactions happening at the time which makes things even more complicated. Hypersonic propulsion systems like the Shock-Induced Combustion Ramjet or SHCRAMJET. Because of such complex physical implications of the flow, it was necessary to use computational tools for simulations and analysis of the propulsion system.

This work is dedicated to the development of a three-dimensional computational fluid dynamics (CFD) solver tailored for reactive hypersonic flows. The solver is built within the AMReX framework and designed using object-oriented principles to ensure modularity, extensibility, and high-performance computing capabilities.The physical modeling includes multi-species compressible Navier-Stokes equations, high-temperature thermodynamics based on NASA-9 polynomials, vibrational non-eqilibrium, a two-temperature formulation.

High-resolution shock-capturing schemes are employed to accurately resolve discontinuities and detonation-like structures typical of supersonic combustion.The numerical implementation has been validated through a sequence of test cases ranging from multispecies shock tubes and shock-ramp interactions to oblique detonation configurations, non-reactive scramjet inlets, combustion-driven shock tube problems.

The goal of this work is to provide a robust and reliable numerical tool capable of investigating shock-induced combustion mechanisms in SHCRAMJET configurations, contributing to a deeper understanding of ignition processes, flame stabilization, and non-equilibrium effects in high-enthalpy supersonic propulsion systems.