Literature regarding hypersonic shock/boundary-layer interaction is mostly restricted to calorically perfect gases, even though this condition is far from reality when temperature rises. High-temperature effects alter physical and transport properties of the fluid, due to vibrational excitation and gas dissociation, and chemical reactions must be considered in order to compute the flow field. In this work, a code for hypersonic aerodynamics with reactions using parallel machines (CHARLIE) is described and a numerical methodology is developed to perform direct numerical simulations of shock/boundary-layer interaction in chemical nonequilibrium. The numerical scheme and the characterization of non-reflecting boundary conditions are addressed. Results show that the flow properties differ considerably if chemical reactions are taken into account. A direct numerical simulation of a shock interacting with a turbulent boundary layer in the hypersonic regime with high-temperature effects is also presented for the first time.

有关高超音速激波/边界层相互作用的文献大多仅限于热量完美的气体，尽管当温度升高时这种情况远非现实。由于振动激发和气体离解，高温效应会改变流体的物理和传输特性，必须考虑化学反应才能计算流场。在这项工作中，高超音速空气动力学的代码与使用平行机器的反应（查理) 进行了描述，并开发了一种数值方法来执行化学非平衡状态下冲击/边界层相互作用的直接数值模拟。讨论了数值方案和非反射边界条件的表征。结果表明，如果考虑化学反应，流动特性会有很大差异。还首次提出了具有高温效应的高超声速状态下激波与湍流边界层相互作用的直接数值模拟。