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Numerical investigation of chemically reacting flows in ramjet dump combustorsThe time-dependent Navier-Stokes equations, including second-order turbulence model, are numerically integrated by using four-stage Runge-Kutta scheme to predict the steady-state supersonic flow structures in ramjet dump combustors. The formulation is derived for reacting flows with finite-rate chemistry. In the present study, it is firstly attempted to assess the accuracy of existing high-order turbulence model in supersonic flows. The comparison shows reasonable agreement between calculated and measured data in terms of velocity distributions. It is indicated that a modified constant C-mu for calculating turbulent eddy viscosity is needed in the supersonic flow regime and the adaptive meshing is preferred to capture the recirculation zone. In the reacting flow calculation, the results from a test case of hydrogen and air combustion at premixed conditon show that the rearward facing step is able to increase flow residence time and stabilize the flame in supersonic flows.
Document ID
19890041037
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Hsieh, Kwang-Chung
(NASA Lewis Research Center; Sverdrup Technology, Inc. Cleveland, OH, United States)
Liu, Jong-Shang
(Textron Lycoming Stratford, CT, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1989
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
AIAA PAPER 89-0387
Accession Number
89A28408
Distribution Limits
Public
Copyright
Other

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