BEGIN:VCALENDAR VERSION:2.0 PRODID:-//linuxsoftware.nz//NONSGML Joyous v1.4//EN BEGIN:VEVENT SUMMARY:Aerothermodynamic of Supersonic Combustion Processes in Shock-Indu ced\, High Enthalpy Flows DTSTART:20260223T110000Z DTEND:20260223T130000Z DTSTAMP:20260908T201706Z UID:a7d8d6f6-2576-4592-8dbe-e73dbd02d4ac SEQUENCE:2 CREATED:20260219T091727Z DESCRIPTION:Hypersonic propulsion systems have to deal with extreme flow c onditions like strong shock waves and very high temperatures\, leading to high enthalpy flows. This flow also have chemical reactions happening at t he time which makes things even more complicated. Hypersonic propulsion sy stems like the Shock-Induced Combustion Ramjet or SHCRAMJET. Because of su ch complex physical implications of the flow\, it was necessary to use com putational tools for simulations and analysis of the propulsion system.Thi s work is dedicated to the development of a three-dimensional computationa l fluid dynamics (CFD) solver tailored for reactive hypersonic flows. The solver is built within the AMReX framework and designed using object-orien ted principles to ensure modularity\, extensibility\, and high-performance computing capabilities.The physical modeling includes multi-species compr essible Navier-Stokes equations\, high-temperature thermodynamics based on NASA-9 polynomials\, vibrational non-eqilibrium\, a two-temperature formu lation. High-resolution shock-capturing schemes are employed to accurately resolve discontinuities and detonation-like structures typical of superso nic combustion.The numerical implementation has been validated through a s equence 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 t o provide a robust and reliable numerical tool capable of investigating sh ock-induced combustion mechanisms in SHCRAMJET configurations\, contributi ng to a deeper understanding of ignition processes\, flame stabilization\, and non-equilibrium effects in high-enthalpy supersonic propulsion system s. LAST-MODIFIED:20260219T092330Z LOCATION:Sala de Formação Avançada do Departamento Física (2-8.11) URL:http://df.vps.tecnico.ulisboa.pt/pt/eventos/aerothermodynamic-of-super sonic-combustion-processes-in-shock-induced-high-enthalpy-flows/ X-ALT-DESC;FMTTYPE=text/html:

Hypersonic propulsi on systems have to deal with extreme flow conditions like strong shock wav es 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 Co mbustion Ramjet or SHCRAMJET. Because of such complex physical implication s of the flow\, it was necessary to use computational tools for simulation s and analysis of the propulsion system.

This work is dedicated t o the development of a three-dimensional computational fluid dynamics (CFD ) solver tailored for reactive hypersonic flows. The solver is built withi n the AMReX framework and designed using object-oriented principles to ens ure modularity\, extensibility\, and high-performance computing capabiliti es.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.

Hig h-resolution shock-capturing schemes are employed to accurately resolve di scontinuities and detonation-like structures typical of supersonic combust ion.The numerical implementation has been validated through a sequence of test cases ranging from multispecies shock tubes and shock-ramp interactio ns to oblique detonation configurations\, non-reactive scramjet inlets\, c ombustion-driven shock tube problems.

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

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