Yu Huanli

TL;DR: In this paper, the three-dimensional coupled implicit Reynolds average Navier-Stokes (RANS) equations, SST k - ω turbulent model and Eddy-Dissipation Concept (EDC) reaction model are employed to investigate the flow fields with different mixer configurations, namely the lobe, rectangle, triangle, and pentagon.

TL;DR: In this article, an inclined injection system with a cavity and grooves arranged in series is developed to enhance the supersonic mixing in a scramjet combustor, and the numerical results reveal that the grooved configuration has a significant influence on the flow field structure.

TL;DR: In this paper, the effects of the secondary fuel jet on the flow field structure and mixing enhancement performance are discussed by changing both the SFL angle and spacing of multiple rows of jet holes.

TL;DR: In this article, a hot-fire test was conducted to demonstrate the flow characteristics of the rocket-ejector system with the limited mixer length, and the results showed that shortening the length of the mixer length reduces the critical backpressure of the RS-1E.

TL;DR: In this paper, the effect of different supersonic airflow conditions on the flow field is discussed. And the results reveal that the shear layer between the airflow and the rocket gases gradually slopes downward with the increase of Mach number.

TL;DR: An alternating-lobe nozzle with nail-like crests and sword deep valleys (NSALN-1) was modified to achieve the ultimate mixing efficiency by enhancing the mixing in the core region.