A Caltech Library Service

An investigation of a contoured wall injector for hypervelocity mixing augmentation

Waitz, Ian-A and Marble, Frank E. and Zukoski, Edward E. (1991) An investigation of a contoured wall injector for hypervelocity mixing augmentation. AIAA Papers, AIAA 91-2265 . American Institute of Aeronautics and Astronautics .

[img] PDF - Published Version
See Usage Policy.


Use this Persistent URL to link to this item:


An experimental and computational investigation of a contoured wall fuel injector is presented. The injector was aimed at enabling shock-enhanced mixing for the supersonic combustion ramjet engines currently envisioned for applications on hypersonic vehicles. Three-dimensional flow field surveys, and temporally resolved planar Rayleigh scattering measurements are presented for Mach 1.7 helium injection into Mach 6 air. These experimental data are compared directly with a three-dimensional Navier-Stokes simulation of the flow about the injector array. Two dominant axial vorticity sources are identified and characterized. The axial vorticity produced strong convective mixing of the injectant with the freestream. Shock-impingement was particularly effective as it assured seeding of baroclinic vorticity directly on the helium/air interface. The vorticity coalesced into a counter-rotating vortex pair of a sense which produced migration of the helium away from the wall. The influences of spatial averaging on the representation of the flow field as well as the importance of the fluctuating component of the flow in producing molecularly-mixed fluid are addressed.

Item Type:Report or Paper (Report)
Additional Information:© 1991 American Institute of Aeronautics and Astronautics, Inc. All rights reserved. For permission to copy or republish, contact American Institute of Aeronautics and Astronautics. Funding for this work was provided largely through NASA Grant NAG 1-842. The authors wish to thank many members of the technical staff at NASA Langley Research Center. particularly Dennis Bushnell. members of the Experimental Flow Physics Branch, and members of the Computational Methods Branch. The Rayleigh scattering data were obtained through a collaborative effort with B. Shirinzadeh. J. Balla. M. Hillard and R. Exton of the Instrument Research Division's Optical Spectroscopy Section. Supercomputing support was provided by the San Diego Supercomputer Center via a National Science Foundation Grant. the NASA Ames NAS facilities. the JPL/Caltech Cray. and the NASA Langley supercomputing facilities.
Group:Guggenheim Jet Propulsion Center
Funding AgencyGrant Number
Other Numbering System:
Other Numbering System NameOther Numbering System ID
Guggenheim Jet Propulsion CenterUNSPECIFIED
Series Name:AIAA Papers
Issue or Number:AIAA 91-2265
Record Number:CaltechAUTHORS:20101130-101649129
Persistent URL:
Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:21058
Deposited By: Ruth Sustaita
Deposited On:10 Dec 2010 00:42
Last Modified:03 Oct 2019 02:19

Repository Staff Only: item control page