An Experimental Investigation of Cavity Aeroacoustics in High Speed Flows. Appendix A: Supersonic Data. Appendix B: Subsonic Data.

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. (AN)

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1995
Accession Number
ADA298432

Entities

People

  • A. Vakili
  • Paul Nagle
  • Robert R Wolfe

Organizations

  • University of Tennessee Space Institute

Tags

Communities of Interest

  • Cyber
  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Abstracts
  • Aeroacoustics
  • Amplitude
  • Boundaries
  • Boundary Layer
  • Dynamic Pressure
  • Flow
  • Flow Fields
  • Layers
  • Leading Edges
  • Mach Number
  • Materials Science
  • Plastic Explosives
  • Pressure Transducers
  • Trailing Edges
  • Transducers
  • Turbulent Mixing

Fields of Study

  • Physics

Readers

  • Coastal and Marine Engineering/Sediment Transport/Hydraulic Engineering
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow