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A numerical study of candidate transverse fuel injector configurations in the Langley scramjet engineA computer program has been developed that numerically solves the two-dimensional Navier-Stokes and species equations near one or more transverse hydrogen fuel injectors in a scramjet engine. The program currently computes the turbulent mixing and reaction of hydrogen fuel and air, and allows the study of separated regions of the flow immediately preceding and following the injectors. The complex shock-expansion structure produced by the injectors in this region of the engine can also be represented. Results are presented that describe the flow field near two opposing transverse fuel injectors and two opposing staged (multiple) injectors, and comparisons between the two configurations are made to assess their mixing and flameholding qualities.
Document ID
19810026305
Document Type
Conference Paper
Authors
Drummond, J. P. (NASA Langley Research Center Hampton, Va., United States)
Date Acquired
August 11, 2013
Publication Date
September 1, 1980
Subject Category
AIRCRAFT PROPULSION AND POWER
Distribution Limits
Public
Copyright
Other