Modelling of supersonic mixing and shock-wave structure in two jets interaction

Abstract

<span style="font-size:11.0pt;line-height:115%; font-family:" calibri","sans-serif";mso-ascii-theme-font:minor-latin;mso-fareast-font-family:="" "times="" new="" roman";mso-fareast-theme-font:minor-fareast;mso-hansi-theme-font:="" minor-latin;mso-bidi-font-family:"times="" roman";mso-ansi-language:en-us;="" mso-fareast-language:en-us;mso-bidi-language:ar-sa"="">Shock-wave structure due to collision of a hypersonic main jet with a transversely injected side jet and flowfield model for good mixing characteristics were investigated solving two-dimensional complete Navier-Stokes equations. Two flowfield models were considered: (i) upper boundary consists of a wall, named the "confined flow", and (ii) the upper wall was removed making the flowfield as "unconfined". In confined flow the side sonicjet, associated with upper and lower walls, produced a number of non-uniform reflected shock waves and acted as a blockage for the hypersonic main jet resulting in a large subsonic region. To get the supersonic mixing flowfield, we made the flowfield unconfined and increased the Mach number of side jet from <i>M= </i>1.0 to <i>M=2.0. </i>The computer program was verified by the experimental results on the flow pattern of an air jet in a duct with abrupt area enlargement.</span>