HIFiRE-1飞行器激波与边界层干扰气动热研究

To investigate the aerodynamic heating and the shock wave-boundary layer interaction (SWBLI) for hypersonic vehicles with cylinder flare, three-dimensional (3D) numerical simulation of flow field around HIFiRE-1 is carried out based on the finite volume method and Reynolds average Navier-Stokes equations. The performance of code and the mesh independence are evaluated by using pressure and heat transfer data from ground test. Simulated results show that the flow conditions and vehicle configurations have effect on the flow states and heat transfer significantly. The increase or decrease in the Reynolds numbers brings about the rapid altering of heat transfer only. The variation of Mach number results in the changes of both the flow structure and the heat transfer. Expanding or narrowing the angle of the flare leads to the diversification of separation bubbles, as well as the heat flux. The reattachment of separated shock wave on the flare is influenced by enlarging or shortening the length of flare, then resulting in the fluctuation of heat transfer.