Abstract:
This paper presents numerical modeling of the interaction of a multiple supersonic jet with a moving obstacle. For the mathematical description of the physical formulation, the Navier-Stokes equations averaged by Favre in a non-stationary formulation were used. Chimera meshes were used for modeling of moving boundaries. The calculation method was implemented using the OpenFOAM open-source software. Testing of the calculation method showed good agreement with the experimental data of other authors and numerical data using a regular mesh. A conical nozzle with the Mach number of $4.5$ at the outlet was used for the parametric study. The calculation was performed up to the time $t = 0.2$ s; the speed of the obstacle was $1$ m/s. It is obtained that up to $0.01$ s the maximum pressure on the barrier increases, then decreases. At the critical point up to the time of $0.018$ s, there are insignificant pressure fluctuations. Then, there is an increase caused by a decrease in pressure at the intersection of the planes of symmetry of the propulsion system and the obstacle.
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