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Characterization of Chevron Nozzle Performance The flow fields from a set of 50.8 mm diameter circular nozzles were characterized using both streamwise and cross-stream 3-component Stereo Particle Image Velocimetry (SPIV). The test matrix of nozzles included 15 different chevron nozzle designs and one baseline, circularly symmetric nozzle. Nozzle jet operating conditions ranged from acoustic Mach numbers of 0.9 to 1.5, with static temperature ratios ranging between 0.84 and 2.7. Detailed surveys of the single jet flows were performed to capture three-dimensional features of the turbulent exhaust jet evolution. Cross-flow planar measurements were obtained at twelve axial locations, ranging from 0.1 to 20 nozzle diameters downstream of the nozzle exit planes. Streamwise measurements, along the jet centerlines, were obtained at ten partially overlapping downstream locations, providing complete axial surveys over a region extending beyond 20 nozzle diameters downstream of the nozzle exit planes. In both optical configurations, the measurement planes were sized to completely capture the fully turbulent jet shear layer growth. The measured three-dimensional mean and turbulent velocity fields, along with computed second order statistics including axial vorticity and turbulent kinetic energy, were evaluated for all test points. Well-defined streamwise vortex structures in the jet shear layers were measured and reported.
Document ID
Document Type
Technical Memorandum (TM)
Mark P Wernet
(Glenn Research Center Cleveland, Ohio, United States)
James E Bridges
(Glenn Research Center Cleveland, Ohio, United States)
Date Acquired
August 8, 2021
Publication Date
September 24, 2021
Subject Category
Instrumentation And Photography
Report/Patent Number
Funding Number(s)
WBS: 109492.
Distribution Limits
Work of the US Gov. Public Use Permitted.
Technical Review
Single Expert
Jet Noise
Particle Image Velocimetry
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