NEAR WAKE FLOW STUDIES IN SUPERSONIC FLOW

Abstract

The theoretical and experimental investigations carried out on supersonic flow over two-dimensional and axially symmetric base type separated flows are summarized in this report. Correlating equations for base pressure and backward facing step pressure with laminar and turbulent separation are presented. These relations are obtained from considerations of the analysis based on the integral method and experimental data. Measurements of total pressure and temperature profiles in the near wake of a two-dimensional wedge- flat plate model at M=3.5 indicate high recovery temperatures at the outer regions of the wake beyond the neck position. The development of the shock tunnel and its associated equipment is reported, including an improved method for thin film resistance thermometers calibration.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1965
Accession Number
AD0617943

Entities

People

  • Josef Rom

Organizations

  • Technion – Israel Institute of Technology

Tags

Communities of Interest

  • Advanced Electronics

DTIC Thesaurus Topics

  • Accuracy
  • Air Force
  • Base Pressure
  • Boundary Layer
  • Computational Fluid Dynamics
  • Flow Fields
  • Fluid Dynamics
  • Heat Transfer
  • Measurement
  • Pressure Distribution
  • Pressure Measurement
  • Reynolds Number
  • Shock Tunnels
  • Test And Evaluation
  • Turbulent Flow
  • Turbulent Mixing
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Fluid Mechanics and Fluid Dynamics.
  • Thermal Physics or Thermal Science.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow