FLOW FIELD OF A SONIC JET EXHAUSTING COUNTER TO A LOW DENSITY SUPERSONIC AIRSTREAM

Abstract

The flow field of a sonic jet exhausting counter to a supersonic airstream was investigated theoretically and experimentally. The total shock- layer thickness was calculated using a blunt-body-type analysis and the known properties of a free-jet expansion from a sonic orifice. The total shock-layer thickness and position of the outer shock relative to the orifice are shown to be a function of free-stream Mach number, jet reservoir pressure, free-stream pitot pressure, and orifice size. The predicted inner shock position is compared with previously published experimental data, and the predicted outer shock position is compared with data obtained in a low density wind tunnel. Results in the transitional flow regime indicate that the outer shock to orifice position distance is greater than the predicted value.

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Document Details

Document Type
Technical Report
Publication Date
Oct 01, 1967
Accession Number
AD0659372

Entities

People

  • Robert A. Cassanova

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Space
  • Weapons Technologies

DTIC Thesaurus Topics

  • Air Force
  • Blunt Bodies
  • Boundary Layer
  • Experimental Data
  • Flow
  • Flow Fields
  • Flow Visualization
  • Fluid Dynamics
  • Fluid Flow
  • Free Stream
  • Gas Flow
  • Geometry
  • Jet Flow
  • Low Density
  • Mach Number
  • Pressure Distribution
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.
  • Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow