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Thermophysics and Aeromechanics

2018 year, number 1

Numerical simulation of the flow with a pseudo-shock in an axisymmetric expanding duct with a frontal inlet

I.I. Mazhul1,2В and Yu.P. Gounko1

1Khristianovich Institute of Theoretical and Applied Mechanics SB RAS, В Novosibirsk, Russia

2Novosibirsk State Technical University, Novosibirsk, Russia


Keywords: axisymmetric supersonic flow, frontal inlet of internal compression, expanding diffus-er, pseudo-shock, duct throttling


The results of the numerical modeling of a flow with a pseudo-shock in an axisymmetric duct are presented. The duct included a frontal inlet with the initial funnel-shaped compression part and the cylindrical throat part as well as the subsequent expanding diffuser. To create a flow with a pseudo-shock, the duct was throttled with the use of the outlet converging insert. Numerical computations of the axisymmetric flow have been conducted on the basis of the solution of the Reynolds-averaged NavierStokes equations and with the use of the k-ω SST turbulence model. As a result of computations, such parameters of the flow were determined as the location of the beginning of the pseudo-shock, the length of its supersonic part, the velocity profiles in different cross sections of the pseudo-shock, the pressure distribution on the duct wall, the total pressure recovery factor, and others. The behavior of these parameters at the freestream Mach number М = 6 was analyzed versus the diffuser opening angle and different degree of the inlet duct throttling.

DOI: 10.1134/S0869864318010031