Banca de DEFESA: JONATHA WALLACE DA SILVA ARAÚJO

Uma banca de DEFESA de MESTRADO foi cadastrada pelo programa.
STUDENT : JONATHA WALLACE DA SILVA ARAÚJO
DATE: 14/11/2019
TIME: 14:00
LOCAL: Sala 409 do CTEC - UFRN
TITLE:

Computational study of the air capture section of a Scramjet demonstrator

KEY WORDS:

Scramjet, compression section, analytical study, numerical simulation, FLUENT – ANSYS

PAGES: 82
BIG AREA: Engenharias
AREA: Engenharia Mecânica
SUBÁREA: Engenharia Térmica
SPECIALTY: Termodinâmica
SUMMARY:

The use of air breathing propulsion based on supersonic combustion (scramjet technology) is currently seen in the aerospace sector as a promising application in the area of access to space. The main advantages of using this technology compared to current aerospace propulsion systems are the need for no transport of the oxidant, which leads to a reduction in vehicle weight, and a relatively greater specific thrust than conventionally used in rocket engines. Scramjet engines are airbreathing propulsion systems without moving parts that use shock waves established on the structure to compress and decelerate the atmospheric air flow, creating thermodynamic conditions suitable for the combustion to occur at supersonic speed in the combustion chamber of the vehicle, providing a subsequent gas expansion and impulse generation. In this work, analytical and numerical methodologies applied to the design of the air capture section of a scramjet demonstrator are presented and subsequently used in the design and creation of a physical model to demonstrate the technology of supersonic combustion through an atmospheric flight coupled to a rocket motor at a corresponding velocity to Mach number 6.8 at the geometric altitude of 30 km. Computational fluid dynamics simulations (non viscous and viscous flow) are used to verify flow characteristics on the developed model. The simulations with non viscous consideration are compared with analytical theory, also presented in this work. The FLUENT - ANSYS software is used in the computational simulations. The non viscous flow model is initially used in order to present geometric aspects such as shock wave capture as well as aero-thermodynamic evaluation, later k-kl-omega turbulence model is used for the modeling of the viscous flow and adequacy of the model geometry due to the appearance of phenomena associated to the interaction of shock waves with established boundary layer.

BANKING MEMBERS:
Externa à Instituição - HEIDI KORZENOWSKI - UNIVAP
Presidente - 209696 - PAULO GILBERTO DE PAULA TORO
Externo ao Programa - 1647050 - SANDI ITAMAR SCHAFER DE SOUZA
Interno - 3061606 - THIAGO CARDOSO DE SOUZA