THE PERFORMANCE OF A CONVERGENT-DIVERGENT NOZZLE IN A SHOCK TUBE,

Abstract

An investigation was conducted to determine the performance of a Mach 4, converging-diverging, sharp-edge-throat nozzle modification to the Mechanical Engineering Department shock tube. Mach Number measurements were made in the exit plane of the nozzle with a two-dimensional wedge and flow field pictures were recorded using a folded Schlieren system and high-speed motion picture photography. (Author)

Document Details

Document Type
Technical Report
Publication Date
Aug 01, 1963
Accession Number
AD0419597

Entities

People

  • Robert Kincaid Wright

Organizations

  • Air Force Institute of Technology

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Cameras
  • Convergent Divergent Nozzles
  • Engineering
  • Flow Fields
  • Mach Number
  • Mechanical Engineering
  • Motion Picture Photography
  • Motion Pictures
  • Nozzles
  • Photographic Equipment
  • Photographic Materials
  • Photographic Recording Media
  • Photographs
  • Photography
  • Shock Tubes
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Combustion Dynamics and Shock Wave Physics.
  • Combustion and Flow Dynamics.