Investigation of Subsonic Annular Nozzles for Engine Exhaust/External Flow Interaction Studies

Abstract

The results of an experimental investigation to determine the feasibility of conducting engine/external flow interaction tests in subsonic annular airstreams are presented. A representative afterbody model with a 4-in.- diam cylindrical forebody, a faired 15-deg boattail, and a 2.68-in.-diam solid body plume simulator was tested in an 8- by 6-ft porous wall wind tunnel and in annular jets produced by 6-, 8-, and 12-in.-diam nozzles. Afterbody Mach number distributions and boattail pressure drag coefficients obtained on the afterbody in the annular jet were compared with wind tunnel results obtained with boattail approach Mach numbers between 0.5 and 1.0. Boundary-layer profiles were also obtained during the wind tunnel and the annular jet tests.

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Document Details

Document Type
Technical Report
Publication Date
Dec 01, 1976
Accession Number
ADA033932

Entities

People

  • R. J. Matz

Organizations

  • Arnold Engineering Development Complex

Tags

Communities of Interest

  • Materials and Manufacturing Processes
  • Weapons Technologies

DTIC Thesaurus Topics

  • Afterbodies
  • Air Force
  • Boundaries
  • Boundary Layer
  • Engineering
  • Mach Number
  • Measurement
  • Pressure Distribution
  • Pressure Measurement
  • Simulators
  • Static Pressure
  • Test And Evaluation
  • Test Facilities
  • Turbines
  • Wind Tunnel Models
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Electrical Engineering
  • Fluid Dynamics.