HIFiRE-1飞行器激波与边界层干扰气动热研究

高超声速飞行器存在典型的激波与边界层干扰，由此产生的流动分离与再附会带来严重的气动加热问题。采用雷诺平均方法对HIFiRE-1飞行器激波与边界层干扰气动热进行了数值模拟。讨论雷诺数、马赫数等来流参数和飞行器裙体张角、裙体长度等结构参数对气动热的影响，并分析其影响机理。研究结果表明：柱裙拐角处由于存在边界层分离、再附及强烈的激波干涉，导致飞行器壁面存在严重的气动热问题，控制边界层分离和流场结构能有效控制飞行器壁面热环境。改变来流参数和结构参数会对边界层分离、再附和流场结构带来较大影响,具体表现为：来流雷诺数变化时流场结构变化较小，但会大幅度影响再附热流密度；来流马赫数变化时分离激波与飞行器壁面夹角发生变化，相应的气动热有较大变化；裙体张角变化时引起分离区尺度变化，进而改变壁面热流分布；裙体长度变化时影响边界层分离、再附特性，导致壁面热流分布发生变化。

Research on Aero Thermodynamics and Influencing Factors for HIFiRE-1

To investigate the aerodynamic heating and the shock wave-boundary layer interaction (SWBLI) for hypersonic vehicles with cylinder flare,three-dimensional (3 D) 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.