SST Technology Follow-On Program - Phase 2. Noise Suppressor/Nozzle Development. Volume 9. Performance Technology - Analysis of the Low Speed Performance of Multitube Suppressor/Ejector Nozzles (0-167 kn)

Abstract

The effects of geometric variables on the performance of multitube suppressor/ejector nozzles are described and quantified for static and low forward velocity cases. The bulk of the investigation concentrates on configurations compatible with supersonic transport engine exhaust systems. Experimental results are presented for 28 related, model-scale suppressor/ ejector configurations tested at nozzle pressure ratios from 2 to 4 over a range of velocities from 0 to 167 kn. High static performance and minimum lapse rate are shown to be compatible through the proper selection of suppressor/ejector geometry and the optimum ejector inlet area.

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Document Details

Document Type
Technical Report
Publication Date
Mar 01, 1975
Accession Number
ADB004736

Entities

People

  • D. B. Morden
  • R. S. Armstrong

Organizations

  • Boeing

Tags

DTIC Thesaurus Topics

  • Acquisition
  • Aircrafts
  • Airplanes
  • Boundary Layer
  • Commercial Aircraft
  • Data Acquisition
  • Exhaust Systems
  • Gas Turbine Nozzles
  • Geometry
  • Lapse Rate
  • Nozzle Area Ratio
  • Pressure Measurement
  • Skin Friction
  • Static Pressure
  • Supersonic Transport Aircraft
  • Test Facilities
  • Wind Tunnels

Readers

  • Acoustics.
  • Fluid Mechanics and Fluid Dynamics.
  • Software Engineering

Technology Areas

  • Hypersonics