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Modeling scramjet combustor flowfields with a grid adaptation schemeThe accurate description of flow features associated with the normal injection of fuel into supersonic primary flows is essential in the design of efficient engines for hypervelocity aerospace vehicles. The flow features in such injections are complex with multiple interactions between shocks and between shocks boundary layers. Numerical studies of perpendicular sonic N2 injection and mixing in a Mach 3.8 scramjet combustor environment are discussed. A dynamic grid adaptation procedure based on the equilibration of spring-mass system is employed to enhanced the description of the complicated flow features. Numerical results are compared with experimental measurements and indicate that the adaptation procedure enhances the capability of the modeling procedure to describe the flow features associated with scramjet combustor components.
Document ID
19950053432
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Ramakrishnan, R.
(Analytical Services & Materials, Inc. Hampton, VA, United States)
Singh, D. J.
(Analytical Services & Materials, Inc. Hampton, VA, United States)
Date Acquired
August 16, 2013
Publication Date
May 1, 1994
Publication Information
Publication: AIAA Journal
Volume: 32
Issue: 5
ISSN: 0001-1452
Subject Category
Fluid Mechanics And Heat Transfer
Accession Number
95A85031
Funding Number(s)
CONTRACT_GRANT: NAS1-19320
Distribution Limits
Public
Copyright
Other

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