Unsteady Transonic Diffuser Flows in a Two-Dimensional Diffuser.
Annual rept. 1 Apr 77-31 Mar 78,
MCDONNELL DOUGLAS RESEARCH LABS ST LOUIS MO
Pagination or Media Count:
The present study is part of a continuing investigation of unsteady, transonic diffuser flows, with application to dynamic distortion in the inlets of fighter aircraft and airbreathing missile propulsion systems. The investigation is focused on a simple, two-dimensional diffuser configuration displaying a weak shock shortly downstream of the throat Figure 1. Flows in this model were found to display self-excited oscillations involving the shock and the entire subsonic flow behind it. The shock displacement amplitudes are comparable to the throat height and occur at frequencies characterized by the flow speed and the length of the divergent diffuser section. The time-mean and fluctuating properties of this flow and the dependence of these properties on shock strength have been documented.
- Fluid Mechanics
- Air Breathing Engines (Unconventional)