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A Systematic Experimental and Computational Investigation of a Class of Contoured Wall Fuel Injectors

Waitz, Ian A. and Marble, Frank E. and Zukoski, Edward E. (1992) A Systematic Experimental and Computational Investigation of a Class of Contoured Wall Fuel Injectors. AIAA Papers, AIAA 92-0625. American Institute of Aeronautics and Astronautics . http://resolver.caltech.edu/CaltechAUTHORS:20101130-132815278

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Abstract

The performance of a particular class of fuel injectors for scramjet engine applications is addressed. The contoured wall injectors were aimed at augmenting mixing through axial vorticity production arising from interaction of the fueVair interface with an oblique shock. Helium was used to simulate hydrogen fuel and was injected at Mach 1.7 into a Mach 6 airstream. The effects of incoming boundary layer height. injector spacing, and injectant to freestream pressure and velocity ratios were investigated. Results from threedimensional flow field surveys and Navier-Stokes simulations are presented. Performance was judged in terms of mixing, loss generation and jet penetration. Injector performance was strongly dependent on the displacement effect of the hypersonic boundary layer which acted to modify the effective wall geometry. The impact of the boundary layer varied with injector array spacing. Widely-spaced arrays were more resilient to the detrimental effects of large boundary layers. Strong dependence on injectant to free stream pressure ratio was also displayed. Pressure ratios near unity were most conducive to losseffective mixing and strong jet penetration. Effects due to variation in mean shear associated with non-unity velocity ratios were found to be secondary within the small range of values tested.


Item Type:Report or Paper (Report)
Additional Information:© 1992 American Institute of Aeronautics and Astronautics. Inc. All rights reserved. Funding for this work was provided largely through NASA Grant NAG 1-842. The fundamentals of shock-enhanced mixing were developed earlier under Contract F49620-86-C-0113 administered by the Air Force Office of Scientific Research. The authors wish to thank many members of the technical staff at NASA Langley Research Center, particularly D. Bushnell, S. Robinson. M. Walsh, members of the Experimental Flow Physics Branch, and members of the Computational Methods Branch. The planar Rayleigh scattering data alluded to at several points in the discussion were the product of a collaborative effort with the Optical Spectroscopy Section of NASA Langley's Instrument Research Division. 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
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Other Numbering System NameOther Numbering System ID
Guggenheim Jet Propulsion CenterUNSPECIFIED
AIAA92-0625
Record Number:CaltechAUTHORS:20101130-132815278
Persistent URL:http://resolver.caltech.edu/CaltechAUTHORS:20101130-132815278
Official Citation:A systematic experimental and computational investigation of a classof contoured wall fuel injectors WAITZ, IAN A., California Institute of Technology, Pasadena; MARBLE, FRANK E., California Institute of Technology, Pasadena; ZUKOSKI, EDWARD E., California Institute of Technology, Pasadena AIAA-1992-625 Aerospace Sciences Meeting and Exhibit, 30th, Reno, NV, Jan 6-9, 1992. 22 p
Usage Policy:No commercial reproduction, distribution, display or performance rights in this work are provided.
ID Code:21069
Collection:CaltechAUTHORS
Deposited By: Ruth Sustaita
Deposited On:10 Dec 2010 00:28
Last Modified:26 Dec 2012 12:41

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