An Experimental Investigation of Downstream Flow-Field Properties Behind a Forward Located Sonic Jet Injected into Transonic Freestream from a Body of Revolution

Abstract

Transonic wind-tunnel investigation was conducted to determine the nature of the flow field downstream of a lateral sonic jet on a body of revolution. The survey was made in a plane normal to the body centerline 9.25 body diameters aft of the lateral jet nozzle. Velocity measurements were made by a remotely driven Pitot-static probe at wind-tunnel Mach numbers of 0.9 and 1.2. The data are presented in the form of Mach number vectors mapped in the normal plane for three pressure ratios and for model angles of attack of 0.0 and 1.0 deg.

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Document Details

Document Type
Technical Report
Publication Date
Jan 01, 1968
Accession Number
AD0718246

Entities

People

  • C. W. Dahlke

Tags

Communities of Interest

  • Weapons Technologies

DTIC Thesaurus Topics

  • Accuracy
  • Cartesian Coordinates
  • Cross Flow
  • Diameters
  • Flow
  • Flow Fields
  • Geometry
  • Mach Number
  • Measurement
  • Plenum Chambers
  • Pressure Measurement
  • Revolutions
  • Static Pressure
  • Trailing Vortices
  • Transonic Wind Tunnels
  • Vortices
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Combustion and Flow Dynamics.
  • Fluid Dynamics.