摘要: Accurate and efficient evaluation of thermal loads is important in the analysis of hypersonic flight test articles such as the one flown during the BoLT-Ⅱ flight experiment. The challenge with such a thermal analysis is that the ... 展开 Accurate and efficient evaluation of thermal loads is important in the analysis of hypersonic flight test articles such as the one flown during the BoLT-Ⅱ flight experiment. The challenge with such a thermal analysis is that the aerostructure will typically not reach a thermal steady-state during the flight experiment. This is a consequence of the changing flight conditions along the trajectory and the slow thermal response of the aerostructure's material. To achieve sufficiently accurate predictions it is generally necessary to employ a conjugate heat transfer solver in which a fluid solver computes the flow field over the vehicle and a solid solver computes the transient heat conduction into the vehicle body. In hypersonic flows, it is possible to exploit the relatively fast response of the flow field by assuming that the fluid reaches a steady-state at each discrete point along the trajectory. By doing so, the flow field may be efficiently converged using an implicit method. However, the slow response of the solid domain requires time-accurate integration to accurately capture the transient heat conduction. In this paper, we will demonstrate that an explicit Super-Time-Stepping scheme can significantly reduce the computational time required to simulate the transient heat conduction. We believe this technique is not widely known in the hypersonics simulation community. We use loose temporal coupling between the fluid and solid domains, as mentioned above. We present the formulation and implementation of the solver into Eilmer, and demonstrate its applicability for simulating hypersonic aerothermal problems via validation of the solver. The goal of this work is to demonstrate how we have mitigated the computational expense associated with trajectory-based conjugate heat transfer simulations by applying our solver to the aerothermal analysis of the BoLT-Ⅱ flight experiment. 收起