An Oil Flow Study of a Sonic Reaction Jet Ejecting from a Body of Revolution into a Free Stream of Mach Number Range 1.75 to 4.5

Abstract

An oil flow test was conducted to obtain flow patterns in the vicinity of a transverse sonic jet ejecting from a body of revolution into an oncoming supersonic flow of M = 1.75, 2.0, 3.0, 4.0, and 4.5. The angle of attack was plus or minus 10 degrees with jet total-to-free stream static pressure ratios up to 100. The jet was oriented to various angular positions at several longitudinal body locations.

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Document Details

Document Type
Technical Report
Publication Date
Apr 21, 1970
Accession Number
AD0871755

Entities

People

  • Troy A. Street

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Bow Shock
  • Cameras
  • Export Controls
  • Flow
  • Flow Visualization
  • Free Stream
  • Government (Foreign)
  • Mach Number
  • Photographs
  • Pressure Measurement
  • Static Pressure
  • Supersonic Flow
  • Test Facilities
  • Titanium
  • Titanium Oxides
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Fluid Mechanics and Fluid Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow