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Computational Analysis of the Combustion Processes in an Axisymmetric, RBCC FlowpathComputational fluid dynamic simulations have been used to study the combustion processes within an axisymmetric, RBCC flowpath. Two distinct operating modes have been analyzed to date, including the independent ramjet stream (IRS) cycle and the supersonic combustion ramjet (scramjet) cycle. The IRS cycle investigation examined the influence of fuel-air ratio, fuel distribution, and rocket chamber pressure upon the combustion physics and thermal choke characteristics. Results indicate that adjustment of the amount and radial distribution of fuel can control the thermal choke point The secondary mass flow rate was very sensitive to the fuel-air ratio and the rocket chamber pressure. The scramjet investigation examined the influence of fuel-air ratio and fuel injection schedule upon combustion performance estimates An analysis of the mesh-dependence of these calculations was presented. Jet penetration data was extracted from the three-dimensional simulations and compared favorably with experimental correlations of similar flows. Results indicate that combustion efficiency was very sensitive to the fuel schedule.
Document ID
20010036868
Acquisition Source
Glenn Research Center
Document Type
Conference Paper
Authors
Steffen, Christopher J., Jr.
(NASA Glenn Research Center Cleveland, OH United States)
Yungster, Shaye
(NASA Glenn Research Center Cleveland, OH United States)
Date Acquired
August 20, 2013
Publication Date
November 1, 2000
Publication Information
Publication: JANNAF 25th Airbreathing Propulsion Subcommittee, 37th Combustion Subcommittee and 1st Modeling and Simultation Subcommittee Joint Meeting
Volume: 1
Subject Category
Inorganic, Organic And Physical Chemistry
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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