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) : McCarson, Tillman D., Jr

Report Date : JUN 1968

Pagination or Media Count : 86

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)

Descriptors :   *NOZZLE GAS FLOW, *THRUST VECTOR CONTROL SYSTEMS, COANDA EFFECT, SECONDARY INJECTION, CONVERGENT DIVERGENT NOZZLES, FLUIDICS, WALLS, FLOW SEPARATION, THRUST, TWO DIMENSIONAL FLOW, AXISYMMETRIC FLOW, TEST METHODS, TEST FACILITIES, INSTRUMENTATION, CONFIGURATIONS, THESES.

Subject Categories : Aircraft
      Fluidics and Fluerics

Distribution Statement : APPROVED FOR PUBLIC RELEASE