Gasdynamic and Turbulent Features of Flows with a Pseudo-Shock Wave in Axisymmetric Ducts.

Numerical computations for studying the supersonic flows with a pseudo-shock wave were fulfilled. There was considered an axisymmetric duct including a funnel-shaped inlet, a throat section, a lengthened diffuser, and an outlet throttling section; the freestream flow with a Mach number M = 6 in front of the inlet was preset. There were applied the solvers including the Reynolds-averaged Navier-Stokes code and k-ω SST turbulence model for axisymmetric flows. The main subject of the investigation was determination of effects of the diffuser opening angle θd and the throttling level on forming the flow, gasdynamic and turbulent characteristics of the pseudo-shock wave. Data on variation of the turbulence viscosity along the duct length have shown the possibility of determination of the pseudo-shock wave termination in the diverging ducts instead of the usual method of determination of the pseudo-shock wave length by the distribution of the static pressure along the duct wall which is suitable just only for the non-diverging ducts. [ABSTRACT FROM AUTHOR]