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CFD prediction of the reacting flow field inside a subscale scramjet combustorA three-dimensional, Reynolds-averaged Navier-Stokes CFD code has been used to calculate the reacting flowfield inside a hydrogen-fueled, subscale scramjet combustor. Pilot fuel was injected transversely upstream of the combustor and the primary fuel was injected transversely downstream of a backward facing step. A finite rate combustion model with two-step kinetics was used. The CFD code used the explicit MacCormack algorithm with point-implicit treatment of the chemistry source terms. Turbulent mixing of the jets with the airstream was simulated by a simple mixing length scheme, whereas near wall turbulence was accounted for by the Baldwin-Lomax model. Computed results were compared with experimental wall pressure measurements.
Document ID
19880065924
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Chitsomboon, T.
(Vigyan Research Associates, Inc. Hampton, VA, United States)
Northam, G. B.
(Vigyan Research Associates, Inc. Hampton, VA, United States)
Rogers, R. C.
(Vigyan Research Associates, Inc. Hampton, VA, United States)
Diskin, G. S.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 13, 2013
Publication Date
July 1, 1988
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AIAA PAPER 88-3259
Accession Number
88A53151
Funding Number(s)
CONTRACT_GRANT: NAS1-17919
Distribution Limits
Public
Copyright
Other

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