The study investigates the interaction between a liquid jet and a supersonic crossflow, with emphasis on the transition of the bow shock from regular reflection to Mach reflection. The shock transition is governed by the injection momentum ratio and the compactness ratio, significantly influencing the upstream shock structure, liquid jet penetration, and the resulting flowfield dynamics. 

The study deals with the fluid dynamics during the starting phase of a high altitude testing facility for rocket engines. It is found that the start-up process is governed by the dynamics of recirculation bubble seen in the diffuser. A bubble split-up process during the start-up results in a rapid vacuum pressure generation in the test chamber.

The reflection and refraction of a curved shock front as it propagates along an air-water interface has been investigated. It is found that the shock front transitions from a regular reflection to irregular reflection as the shock front propagates along the interface. A comparison of the shock wave transition conditions over the air water interface and over the solid surfaces has also been carried out.

The asymmetric expansion and shock reflection characteristics in a suddenly expanding duct has been investigated. It is found that the symmetry breaking bifurcation characteristics depends on duct geometry. A novel Mach reflection to regular reflection shock transition has also been observed which depends only on the upstream pressure.