Accession Number:

AD0836804

Title:

STUDY OF THE THRUST PRODUCED BY A COANDA NOZZLE.

Descriptive Note:

Master's thesis,

Corporate Author:

AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING

Personal Author(s):

Report Date:

1968-06-01

Pagination or Media Count:

86.0

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 db from 3 to 8. Author

Subject Categories:

  • Aircraft
  • Fluidics and Fluerics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE