NDLI: Analytical study of mixing and reacting three-dimensional supersonic combustor flow fields

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Analytical study of mixing and reacting three-dimensional supersonic combustor flow fields

Content Provider	NASA Technical Reports Server (NTRS)
Author	Baker, A. J. Rogers, R. C. Zelazny, S. W.
Copyright Year	1975
Description	An analytical investigation is presented of mixing and reacting hydrogen jets injected from multiple orifices transverse and parallel to a supersonic airstream. The COMOC computer program, based upon a finite-element solution algorithm, was developed to solve the governing equations for three-dimensional, turbulent, reacting, boundary-region, and confined flow fields. The computational results provide a three-dimensional description of the velocity, temperature, and species-concentration fields downstream of hydrogen injection. Detailed comparisons between cold-flow data and results of the computational analysis have established validity of the turbulent-mixing model based on the elementary mixing-length hypothesis. A method is established to initiate computations for reacting flow fields based upon cold-flow correlations and the appropriate experimental parameters of Mach number, injector spacing, and pressure ratio. Key analytical observations on mixing and combustion efficiency for reacting flows are presented and discussed.
File Size	4002065
Page Count	65
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19760002928
Archival Resource Key	ark:/13960/t97708728
Language	English
Publisher Date	1975-01-01
Access Restriction	Open
Subject Keyword	Aerodynamics Three Dimensional Flow Supersonic Combustion Ramjet Engines Flow Distribution Mixing Length Flow Theory Supersonic Jet Flow Cold Flow Tests Rocket Engine Design Prediction Analysis Techniques Turbulent Mixing Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Article

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