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Numerical Investigation of Dual-Mode Scramjet Combustor with Large Upstream InteractionDual-mode scramjet combustor configuration with significant upstream interaction is investigated numerically, The possibility of scaling the domain to accelerate the convergence and reduce the computational time is explored. The supersonic combustor configuration was selected to provide an understanding of key features of upstream interaction and to identify physical and numerical issues relating to modeling of dual-mode configurations. The numerical analysis was performed with vitiated air at freestream Math number of 2.5 using hydrogen as the sonic injectant. Results are presented for two-dimensional models and a three-dimensional jet-to-jet symmetric geometry. Comparisons are made with experimental results. Two-dimensional and three-dimensional results show substantial oblique shock train reaching upstream of the fuel injectors. Flow characteristics slow numerical convergence, while the upstream interaction slowly increases with further iterations. As the flow field develops, the symmetric assumption breaks down. A large separation zone develops and extends further upstream of the step. This asymmetric flow structure is not seen in the experimental data. Results obtained using a sub-scale domain (both two-dimensional and three-dimensional) qualitatively recover the flow physics obtained from full-scale simulations. All results show that numerical modeling using a scaled geometry provides good agreement with full-scale numerical results and experimental results for this configuration. This study supports the argument that numerical scaling is useful in simulating dual-mode scramjet combustor flowfields and could provide an excellent convergence acceleration technique for dual-mode simulations.
Document ID
20050041724
Acquisition Source
Headquarters
Document Type
Other
Authors
Mohieldin, T. O. (Old Dominion Univ. Norfolk, VA, United States)
Tiwari, S. N. (Old Dominion Univ. Norfolk, VA, United States)
Reubush, David E. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 7, 2013
Publication Date
December 1, 2004
Subject Category
Spacecraft Propulsion And Power
Report/Patent Number
ODURF-194141
Funding Number(s)
CONTRACT_GRANT: NAG1-2266
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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