SST Technology Follow-On Program - Phase 2. Noise Suppressor/Nozzle Development. Volume 6. Performance Technology - Thrust and Flow Characteristics of a Reference Multitube Nozzle With Ejector

Abstract

Static tests are conducted to establish reference performance levels for a round convergent nozzle and a 3.3 area ratio, 37-tube suppressor nozzle. After assessing bare nozzle performance characteristics, ejector shrouds are added, and the effect of secondary inlet changes and ejector length change on thrust is established. Pressure measurements on nozzle/ejector surfaces are correlated with measured thrust. The secondary flow is measured, and the flow conditions inside the ejectors are established by performing pressure/ temperature traverses.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1975
Accession Number
ADB004733

Entities

People

  • F. Pearlman
  • R. S. Armstrong

Organizations

  • Boeing

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aircrafts
  • Boundaries
  • Boundary Layer
  • Commercial Aircraft
  • Creep
  • Flow
  • Flow Rate
  • High Pressure
  • High Temperature
  • Instrumentation
  • Mass Flow
  • Measurement
  • Pressure Measurement
  • Reynolds Number
  • Secondary Flow
  • Static Pressure
  • Test Facilities

Readers

  • Acoustics.
  • Combustion and Flow Dynamics.