NDLI: Mixing enhancement by tabs in round supersonic jets

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Mixing enhancement by tabs in round supersonic jets

Content Provider	NASA Technical Reports Server (NTRS)
Author	Grosch, C. E. Seiner, John M.
Copyright Year	1998
Description	The objective of this study was to analyze jet plume mass flow entrainment rates associated with the introduction of counter-rotating streamwise vorticity by prism shaped devices (tabs) located at the lip of the nozzle. We have examined the resulting mixing process through coordinated experimental tests and numerical simulations of the supersonic flow from a model axisymmetric nozzle. In the numerical simulations, the total induced vorticity was held constant while varying the distribution of counter-rotating vorticity around the nozzle lip training edge. In the experiment, the number of tabs applied was varied while holding the total projected area constant. Evaluations were also conducted on initial vortex strength. The results of this work show that the initial growth rate of the jet shear layer is increasingly enhanced as more tabs are added, but that the lowest tab count results in the largest entrained mass flow. The numerical simulations confirm these results.
File Size	1219688
Page Count	18
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19980027603
Archival Resource Key	ark:/13960/t3227v632
Language	English
Publisher Date	1998-01-01
Access Restriction	Open
Subject Keyword	Fluid Mechanics And Heat Transfer Computational Fluid Dynamics Prisms Velocity Distribution Counter Rotation Wedges Plumes Shear Layers Navier-stokes Equation Nozzle Geometry Tabs Control Surfaces Mass Flow Rate Vortices Jet Nozzles Vorticity Entrainment Supersonic Jet Flow Mixing Layers Fluids Mass Flow Mach Number Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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