Design and Test of an Annular Sting Support Concept for Aftbody Nozzle Wind Tunnel Testing.

Abstract

The annular sting support concept for aftbody nozzle testing supports the model through the exhaust nozzles, provides high pressure air to simulate the exhaust plume to enter the model, and provides a path for instrumentation lines to be routed out of the model. The support concept, experimental model, and supporting analytical studies are described. Experimental data for the aftbody nozzle contours are compared for a free jet test and the annular sting support test. Also the results of an analytical prediction of the nozzle boattail pressure distribution and wind tunnel wall effects are described. Test results and experimental data comparisons indicate that the annular sting support concept offers an alternate testing technique for aftbody nozzles. (Author)

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1978
Accession Number
ADA056945

Entities

People

  • Douglas L. Bowers

Organizations

  • Flight Dynamics Laboratory

Tags

Communities of Interest

  • Air Platforms
  • Ground and Sea Platforms

DTIC Thesaurus Topics

  • Air Force
  • Air Force Facilities
  • Airframes
  • Boundary Layer
  • Computer Programs
  • Exhaust Nozzles
  • Exhaust Plumes
  • Experimental Data
  • Flow Fields
  • High Pressure
  • Mach Number
  • Pressure Distribution
  • Static Pressure
  • Test Facilities
  • Turbofan Engines
  • Turbojet Engines
  • Wind Tunnels

Fields of Study

  • Physics

Readers

  • Aerodynamics/Aeronautics.
  • Aerospace Propulsion Engineering.
  • Aerospace Test and Evaluation