AN INVESTIGATION OF CONSTANT AREA SUPERSONIC FLOW DIFFUSION

Abstract

Experiments were conducted to determine the nature of the deceleration of supersonic airstreams in straight passages of constant cross sectional area. The magnitude of the losses associated with the recovery of kinetic energy was established, Schlieren observations were made of the field of flow in the passage and the influence of passage length, Mach Number and effective Reynolds Number on maximum obtainable pressure rise were investigated.

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1964
Accession Number
AD0603313

Entities

People

  • Andrew A. Fejer
  • George L. Heath
  • Richard T. Driftmyer

Organizations

  • University of Toledo

Tags

Communities of Interest

  • Energy and Power Technologies
  • Materials and Manufacturing Processes
  • Space

DTIC Thesaurus Topics

  • Air Force
  • Back Pressure
  • Boundary Layer
  • Boundary Layer Trips
  • Complex Systems
  • Diffusion
  • Energy
  • Fluid Flow
  • Jet Propulsion
  • Mach Number
  • Mechanical Engineering
  • Pressure Distribution
  • Static Pressure
  • Supersonic Flow
  • Thermodynamics
  • United States
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Atmospheric Science / Meteorology, specifically Wind Wave Turbulence.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow