Numerical Simulation Of Flow Fields In A Ramjet Isolator With A Divergent Angle

A preliminarily systematic steady and unsteady numerical simulation of shock wave/turbulent boundary-layer interaction phenomenon in a ramjet isolator with a diffuser configuration has been conducted, based on the experimental model adopted by Carroll BF and Dutton JC. The turbulence model suited for simulation of the present problem is selected (S-A turbulence model) by comparison computation, and the influences of back-pressure, Mach number, and turbulent boundary-layer thickness on the structure of shock-train in the isolator are analyzed systematically.The computational results demonstrate that the change of back pressure has no influence on the structure of shock-train and the upstream flow field, but affects its location; Mach number has obvious effect on the structure of shock-train, especially on the symmetry and length of shock-train, spacing and number of shock waves; turbulent boundary-layer thickness has some influence on the location of shock-train and pressure rise ratio through it, but not on its length.