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A systematic experimental and computational investigation of a class of contoured wall fuel injectorsThe performance of contoured wall fuel injectors for scramjet engine applications is considered. These fuel injectors were aimed at augmenting mixing through axial vorticity production arising from interaction of the fuel/air interface with an oblique shock. The effects of incoming boundary layer height, injector spacing, and injectant to freestream pressure and velocity ratios are examined. Results from 3D flow field surveys and Navier-Stokes simulations are presented.
Document ID
19920044383
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Waitz, Ian A.
(NASA Langley Research Center Hampton, VA, United States)
Marble, Frank E.
(NASA Langley Research Center Hampton, VA, United States)
Zukoski, Edward E.
(California Institute of Technology Pasadena, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1992
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AIAA PAPER 92-0625
Accession Number
92A27007
Funding Number(s)
CONTRACT_GRANT: NAG1-842
CONTRACT_GRANT: F49620-86-C-0113
Distribution Limits
Public
Copyright
Other

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