Papers by Keyword: Opposing Jet

Abstract: This paper focus on the detailed influence of forward-facing cavity on the opposing jet. The flow field of a hemisphere nose-tip with the combined configuration was simulated numerically and the surface heat flux distribution was obtained. The numerical results show that a suitable cavity is helpful for the opposing jet. With the same total pressure, the single opposing jet even can’t form a stable flow field and there is no cooling effect.

Abstract: In this paper, the unsteady flow field formed by the hemisphere nose-tip with forward-facing cavity and opposing jet combined thermal protection system (TPS) under high speed free stream flow (Ma4.98) was investigated numerically. The periodic variation of the drag coefficient and the flow field of the nose-tip were obtained. The numerical results show that a suitable cooperation between the opposing jet stream condition and the physical dimension of the cavity is necessary.

Abstract: In this paper, a thermal protection system (TPS) of opposing jet combined with a forward-facing cavity in hypersonic flow was investigated numerically. The flow field parameters and heat flux distribution along the outer body surface are obtained. The thermal protection efficiency of the combined TPS and the single opposing jet TPS was compared. The numerical results shows that this combined TPS has a good effect on cooling the nose of hypersonic vehicle. The recirculation region plays an pivotal role for the reduction of heat flux. The exist of the cavity strengthen the cooling efficiency.