masterThesis
Análise numérica do escoamento na seção de captura de ar de um demonstrador scramjet
Fecha
2019-11-14Registro en:
ARAÚJO, Jonatha Wallace da Silva. Análise numérica do escoamento na seção de captura de ar de um demonstrador scramjet. 2019. 76f. Dissertação (Mestrado em Engenharia Mecânica) - Centro de Tecnologia, Universidade Federal do Rio Grande do Norte, Natal, 2019.
Autor
Araújo, Jonatha Wallace da Silva
Resumen
The use of airbreathing 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 dispensable of transport of the oxidant, which
reduces the vehicle weight, and a relatively greater specific thrust than those conventionally
used in rocket engines. Scramjet engines are airbreathing propulsion systems based on no
moving parts that use shock waves established on these structures to compress and
decelerate the atmospheric air flow, thereby creating thermodynamic conditions suitable for
the combustion to occur at supersonic speed in the combustion chamber of the vehicle and
providing a subsequent gas expansion and impulse generation. In this work, an analytical
and a numerical approach were applied to the design of the air capture section of a scramjet
demonstrator and subsequently used in the design of a physical model to demonstrate the
technology of supersonic combustion through an atmospheric flight coupled to a rocket at a
corresponding velocity of Mach number of 6.8 for a geometric altitude of 30 km. CFD
simulations (non-viscous and viscous flow) were performed to verify the flow
characteristics on the developed model. The simulations with non-viscous consideration
were compared with the results of the analytical theory, presented in this work. The nonviscous flow model was initially used in order to present geometric aspects such the shock
wave capture and the aerothermodynamic evaluation, subsequentially the k-kl-omega
turbulence model was used for the modeling of the realistic viscous flow and its adequacy
due to the appearance of phenomena associated to the interaction of the shock waves with
the viscous boundary layer.