An Experimental Investigation of Cavity Aeroacoustics in High Speed Flows.

Abstract

The research presented in this report has been directed to study the effects of mass injection into the flow upstream of a cavity to understand the weapon bay cavity's flow field and its aeroacoustics. The objective also was to control the development of upstream boundary layer, and therefore, to control the development of the shear layer over the cavity. Control of the shear layer has enabled us to significantly reduce or to fully eliminate the weapons bay's aeroacoustic interactions. This study was performed in a wind tunnel at several nominal Mach numbers between 0.5 to 1.8 and at unit Reynolds numbers up to 17 millions per foot. Measurements were performed for a number of injection distributions. The large amplitude oscillations measured without mass injection was successfully and totally eliminated with proper mass injection.

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1995
Accession Number
ADA298056

Entities

People

  • Ahmad D. Vakili
  • Paul A. Nagle
  • Robert R Wolfe

Organizations

  • University of Tennessee Space Institute

Tags

Communities of Interest

  • Energy and Power Technologies
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Boundaries
  • Boundary Layer
  • Dynamic Pressure
  • Flow Fields
  • Flow Visualization
  • Fluid Dynamics
  • Layers
  • Mach Number
  • Measurement
  • Measuring Instruments
  • Pressure Distribution
  • Pressure Measurement
  • Pressure Transducers
  • Reynolds Number
  • Static Pressure
  • Turbulent Mixing
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Atmospheric Science / Meteorology, specifically Wind Wave Turbulence.
  • Combustion and Flow Dynamics.
  • Computational Fluid Dynamics (CFD)