Development of a Nozzle to Improve the Turning of Supersonic Coanda Jets

Abstract

The hypothesis that shaping the jet velocity profile improved the thrust vectoring of supersonic Coanda jets was experimentally tested. A new nozzle design procedure, based on the method of characteristics, was developed to design a nozzle which delivers an arbitrary exit velocity profile. Such a nozzle was designed for a pressure ratio of 2.5, to provide a jet matched to a circular Coanda surface with radius equal to five jet thicknesses. The thrust vectoring of this nozzle was then compared to that of a convergent divergent nozzle over a range of pressure ratios from 1.5 to 3.5. It is concluded that supersonic nozzles provide greatly improved turning of Coanda jets, and that shaping the velocity profile further improves the thrust vectoring.

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Document Details

Document Type
Technical Report
Publication Date
Apr 01, 1980
Accession Number
ADA087709

Entities

People

  • John D. Lee
  • Paul M. Bevilaqua

Tags

Communities of Interest

  • Air Platforms

DTIC Thesaurus Topics

  • Aeronautical Laboratories
  • Air Force
  • Aircrafts
  • Barometric Pressure
  • Boundary Layer
  • Compression Waves
  • Crystal Structure
  • Flow Visualization
  • Fluid Dynamics
  • Layers
  • Pressure Distribution
  • Pressure Gradients
  • Pressure Measurement
  • Short Takeoff Aircraft
  • Specific Heat
  • Static Pressure
  • Supersonic Flow

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.

Technology Areas

  • Hypersonics
  • Hypersonics - Hypersonic Flow