Numerical investigation of the interaction of twin supersonic jet with a flat obstacle

Abstract

This paper presents the results of mathematical modeling of the interaction of supersonic twin jet flow with a flat obstacle. The influence of the distance between the nozzles on the shock-wave structure of the gas flow for the Mach numbers 4.7 on the nozzle exit are studied. In the studies, the distance from the nozzle exit to obstacle was 0.5 meters, the distance between the nozzles varied from 0.1 to 4.0 nozzle exit diameters. It was found that in the range of distances between nozzles 0.1-1 nozzle exit diameters, the shock-wave structure of the flow and pressure distribution along the obstacle are similar. With an increase in the distance between the nozzles of more than 1.0 nozzle exit diameters the maximum pressure on the obstacle is two times less. For distance 4.0 of nozzle exit dimeter in the region of the triple configuration of shock waves oscillations are observed.