Abstract:
Hypersonic aerodynamic heating causes gas flow in many advanced hypersonic vehicles with contained cavity. It is necessary to accurately simulate hypersonic flow field, structure temperature field, and cavity flow by numerical method for thermal structure analysis. In this paper, a synchronized method for multi-regional simulation in hypersonic flow is developed. Particularly, a hypersonic moving object containing a cavity is our major concern, where the thermal convection in the cavity caused by the external aerothermal/structural heat conduction is investigated. Based on the previously developed synchronized method for external hypersonic flow/structural temperature field coupling, the preconditioning matrix method is adopted in order to further consider the low-speed cavity flow. The virtual boundary cells are introduced on both sides of the interface between the flow field and the structural temperature field, so that the physical information exchange between adjacent fields can be efficiently realized. The present method is first validated through two benchmark cases, then it is further applied to two hypersonic moving annuli with closed and perforated cavities. For the both two annuli, the computed results show that the cavity flows caused by uneven distributions of structural temperature could have a slight influence on the structural temperature field in turn. Under the influence of convective flow in the cavity, the leading edge temperature of the closed ring in 35s decreases by about 0.8%. For the annulus with perforated cavity, the temperature around the hole wall exceeds the stagnation point temperature at the leading edge of the outflow within 0.5s. A numerical method for simulating the structure heat conduction of hypersonic vehicle considering cavity flow is provided.