Performance Tests of the Original Transonic Wind Tunnel Compressor and Circuit

Abstract

A detailed test programme of the AMRL Transonic Wind Tunnel was conducted. The objective of the test programme was to determine the pressure distributions around the tunnel circuit with larger nozzle exit areas. The existing high speed contraction, test section, model support mechanism, and downstream diffuser were removed for the tests. A variable nozzle and collector were designed and installed in place of the removed components to determine the effects of increasing the nozzle exit area. Three nozzle configurations were investigated, with a 38.3%, 44.4% and 58.1% increase in area relative to the existing test section area. Measurements were made of static pressure around the tunnel circuit, total pressure upstream and downstream from the compressor, and temperatures at various locations. Noise measurements were also made outside the tunnel complex and at four locations around the boundary of the site to determine the noise level of the wind tunnel.

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Document Details

Document Type
Technical Report
Publication Date
May 01, 1998
Accession Number
ADA352590

Entities

People

  • Howard A. Quick
  • Yoel Y. Link

Tags

Communities of Interest

  • Advanced Electronics
  • Sensors
  • Space

DTIC Thesaurus Topics

  • Accuracy
  • Acquisition
  • Compressors
  • Computational Fluid Dynamics
  • Data Acquisition
  • Dynamic Pressure
  • Engineering
  • Fluid Dynamics
  • Heat Exchangers
  • Mach Number
  • Measurement
  • Performance Tests
  • Pressure Measurement
  • Static Pressure
  • Tubes
  • Wind Tunnel Tests
  • Wind Tunnels

Fields of Study

  • Engineering

Readers

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