STUDY OF THE THRUST PRODUCED BY A COANDA NOZZLE.

Abstract

An experimental study was performed to determine the influence of geometry on the thrust of a two-dimensional Coanda-effect nozzle and to determine the fluid flow rate required to switch the primary fluid jet by injection parallel to nozzle axis. The thrust varied from 3 to 40 Lbf as nozzle pressure ratio varied from 1.3 to 5.3 for nozzle divergence half-angles from 10 degrees to 20 degrees and ratio of diverging wall spacing at the throat to throat width (d/b) from 3 to 8. (Author)

Document Details

Document Type
Technical Report
Publication Date
Jun 01, 1968
Accession Number
AD0836804

Entities

People

  • Tillman D. Mccarson Jr

Organizations

  • Air Force Institute of Technology

Tags

DTIC Thesaurus Topics

  • Coanda Effect
  • Flow
  • Flow Rate
  • Fluid Flow
  • Geometry
  • Mathematics
  • Two Dimensional

Fields of Study

  • Physics

Readers

  • Combustion and Flow Dynamics.

Technology Areas

  • Space
  • Space - Hall-Effect Thruster