Abstract

This paper presents the results of numerical investigation of the interaction of a single supersonic jet with a flat obstacle. Mach numbers 1.5 and 3 at the nozzle exit with a pressure ratio n=1.34, and the distances h/d=1.8-9.2 from the nozzle exit to obstacle are considered. The influence of the Mach number at the nozzle exit on the shock-wave structure of the flow and the force action of the jet on the obstacle surface are studied. For Mach number 1.5 the maximum pressure on the obstacle surface is located on the axis of the jet. The shock-wave pattern of the flow for Mach number 3 is significantly different from the Mach number 1.5 in the range of the distances h/d=1.8-3.8. With increasing distance for Mach number 3, in the range distances h/d=3.8-5.8, the shock-wave pattern of the gas flow changes and becomes analogous to the cases of calculations for the Mach number 1.5 at the nozzle exit in the range h/d=1.8-3.8. The same for the distances range h/d=5.8-9.2 of the obstacle location are observed. And it is shown that the pressure level depends on the zone of the supersonic jet which located obstacle.

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