Design and optimization of rocket-engine nozzle contours through advanced numerical modeling

The research activity will focus on the design and optimization of rocket-engine nozzle contours, with the aim of improving propulsion performance under different operating conditions. The research will be carried out using numerical simulation tools based on both high-fidelity and reduced-order models. Parametric analyses and comparisons among different geometrical configurations will be performed to identify efficient design solutions. The activity will also include the analysis of nozzle operation under off-design conditions, with particular emphasis on sea-level operation, flow separation phenomena, and their effects on performance and aerodynamic side loads. Finally, numerical methodologies will be developed for nozzle performance assessment and for the evaluation of the main loss mechanisms associated with contour effects, viscous friction, heat transfer, and finite-rate chemical kinetics

Selection process

Qualifications and Interview evaluationin order to get more information and how to apply, please download the announcement, the application form and attached files at link https://web.uniroma1.it/trasparenza/dettaglio_bando_albo/246531 up to 60 points for the relevance and significance of qualifications, publications (max 5) and scientific and professional curriculum vitae - up to 40 points for the interview REQUIREMENT: Master's Degree in Space and Astronautical Engineering PREFERRED SKILLS: The candidate shall have a solid background in space propulsion, with particular emphasis on chemical rocket engines and their underlying physical, thermo-fluid dynamic, and design challenges. Demonstrated knowledge of gas dynamics, compressible and reacting flows, nozzle expansion processes, and the main phenomena affecting nozzle performance, including viscous friction, heat transfer, finite-rate chemical kinetics, and flow separation, is required. The candidate shall also have a thorough knowledge of numerical methods for the solution of the governing equations of compressible and reacting flows, together with documented experience in Computational Fluid Dynamics (CFD), reduced-order modeling, and the design, numerical analysis, and optimization of rocket-engine nozzles

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