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