Large eddy simulation of the HyShot II combustor

Hypersonic flight has the potential to revolutionize the aerospace sector, offering new possibilities for space access and long-range commercial aviation. The primary challenge in achieving sustained hypersonic travel lies in the development of an efficient propulsion system capable of overcoming the extreme aerodynamic drag at such high speeds. Scramjet engines are among the most promising candidates to meet this demand; however, to achieve stable combustion in supersonic flows, the mixing of fuel and air must be optimal. In this work, we present a wall-resolved Large Eddy Simulation (LES) of the cold flow within the HyShot II scramjet combustor. The objective is to investigate the interaction between the turbulent boundary layers developing along the combustor walls and the fuel jet injected crosswise into the supersonic airstream. This study serves as a foundation for future reactive simulations and contributes to a better understanding of mixing mechanisms in realistic scramjet operating conditions.