Transonic Flow in a Sajben Diffuser
Model ID: 10407
In this model the high speed turbulent gas flow in a converging and diverging nozzle is modeled using the High Mach Number Flow interface. The diffuser is transonic in the sense that the flow at the inlet is subsonic, but due to the contraction and the low outlet pressure, the flow accelerates and becomes sonic (Ma = 1) in the throat of the nozzle.
After a short region of supersonic flow, a normal shock wave brings the flow back to subsonic flow. This setup has been studied in a number of experiments and numerical simulations by M. Sajben and co-workers, in an effort to study unsteady fluctuations in supersonic inlets with applications in supersonic aircraft propulsion systems. The geometry and setup is often referred to as a Sajben diffuser and constitutes a common test case for the simulation of high Mach number internal flows.
In this model the time averaged transonic flow through a Sajben diffuser is solved for using two different exit pressures. The flow in the diffuser is fully turbulent with a inlet Reynolds number of 7x105 based on the inlet fluid properties and the channel height. The model uses the Spalart-Allmaras turbulence model to compute the turbulent viscosity.
|A surface plot showing the Mach number, flow streamlines, and zero x-component velocity contour resulting from the weak shock case.|