SST Technology Follow-On Program - Phase 2. Noise Suppressor/Nozzle Development. Volume 8. Performance Technology Multitube Suppressor/Ejector Interaction Effects on Static Performance (Ambient and 1150 F Jet Temperature)

Abstract

The effects of geometric variables and temperature on the static performance of multitube suppressor/ejector exhaust nozzles are described and quantified. Six suppressor and four ejector parameters are investigated to establish the criteria for maximum performance. Results are presented for a model scale test of 102 related suppressor/ejector configurations operated at pressure ratios from 2 to 4 and at ambient and 150 F jet temperatures. Performance trends as a function of geometry are presented in a manner which allows the selection of the best geometry for any desired set of suppression and installation constraints.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1975
Accession Number
ADB004735

Entities

People

  • D. B. Morden
  • R. S. Armstrong

Organizations

  • Boeing

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Accuracy
  • Aircrafts
  • Airplanes
  • Base Pressure
  • Commercial Aircraft
  • Data Acquisition
  • Flow Rate
  • Gas Turbine Nozzles
  • Geometry
  • Instrumentation
  • Nozzle Area Ratio
  • Pressure Distribution
  • Pressure Gradients
  • Pressure Measurement
  • Secondary Flow
  • Static Pressure
  • Supersonic Transport Aircraft

Fields of Study

  • Engineering

Readers

  • Combustion and Flow Dynamics.
  • Nuclear Civil Defense.
  • Organizational Process Management (OPM).