Department of Aerospace Engineering, University of Glasgow
Abstract
Shock reflection hysteresis in a low density, axisymmetric underexpanded air jet is
examined using a Navier-Stokes flow solver. Jets of this type are found in a number
of applications e.g. rocket exhausts. The existence of a dual solution domain where
either regular or Mach reflection may occur within the complex plume structure is
predicted. This is in agreement with experiment where the same phenomenon has
been observed for a nitrogen jet. The results of the computational study are used to
examine the structure of the plume, and are compared with experimental data where
available. The plume structure is complex, involving the interaction of several flow
features, making this a demanding problem. A quasi-steady approach is employed
in order to calculate the entire hysteresis loop. Included in this report is a review
of the two dimensional shock reflection hysteresis problem. Some recommendations
are made for further study of this type of flow
