Showing papers by "Defence Research and Development Laboratory published in 1998"
TL;DR: In this paper, a dual stream supersonic flow facility with a 2D lobed nozzles was studied and the results indicated that an enormous enhancement in mixing was achieved by the 2D nozzle in comparison with a plain 2D nozzle.
Abstract: Studies on mixing enhancement with two dimensional (2D) lobed nozzle have been conducted in a dual stream supersonic flow facility. The distributions of momentum flux, stagnation pressure and stagnation temperature across a plane at different axial distances from the nozzle exit were considered as a measure of mixing. The results indicated an enormous enhancement in mixing when 2D lobed nozzle was employed in comparison with conventional plain 2D nozzle. The enhanced mixing performance could be attributed to the large scale axial vortices observed in the flow-field of subsonic lobed nozzles by earlier investigators.
16 citations
TL;DR: In this article, various methods have been developed for property modification of materials, such as ion implantation, sputtering and combination processes, with particular reference to semi-conductors.
Abstract: The paper describes the various methods that have been developed for property modification of materials. Methods include ion implantation, sputtering and combination processes. Applications are listed with particular reference to semi-conductors.
5 citations
TL;DR: In this paper, the effects of pilot injection, double wall injection and step configuration on the performance of the supersonic combustor were studied in terms of combustion efficiency and stagnation pressure drop.
Abstract: Experimental studies were made on supersonic combustion in a two dimensional combustor using Hydrogen as fuel. A Hydrogen vitiation air heater with oxygen replenishment was used for simulating high temperature air entering the supersonic combustor. Transverse fuel injection was employed from the walls (Single wall and Double wall)of the combustor at upstream (Pilot injection) and downstream (Primary injection) of backward-facing step. Experiments were also conducted with single wall injection and in the absence of step and pilot injection. Ignition and pressure drop characteristics of the combustor were determined. Wall static pressures were considered as a measure to find the advantages of pilot and double wall injections. The effects of pilot injection, double wall injection and the step on the performance of the supersonic combustor were studied in terms of combustion efficiency and stagnation pressure drop. It is found that the combustor with pilot fuel and step configuration, employing doubl...
1 citations