Adaptive Mesh Refinement–Based Numerical Simulation of Detonation Initiation in Supersonic Combustible Mixtures Using a Hot Jet
Publication: Journal of Aerospace Engineering
Volume 28, Issue 1
Abstract
An open-source program implementing a block-structured adaptive mesh refinement method was adopted for the fine structure numerical simulation of detonation initiation in supersonic combustible mixtures. Simulations were conducted on a nested parallel computing system. The initiation process was specified as three stages, and their respective flow field characteristics were analyzed. Results indicate that a hot jet under specific conditions can have a similar effect as a pneumatic oblique bevel for inducing periodical shock-induced detonative combustion by a bow shock. The interaction of bow shock–induced combustion with the local detonation wave, produced by the reflection shock on the upper wall, can create a structure with two triple-wave points. The hot jet not only plays a role in the detonation initiation but also acts as a stabilizing control mechanism for detonation propagation. In the simulations in this study, the detonation wave propagates in an overdriven state initially and achieves self-sustaining motion after the shutdown of the hot jet. Subsequently, the final pisiform structure of typical stable Chapman-Jouguet detonation cells is formed.
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Acknowledgments
This study was supported by the National Natural Science Foundation of China under Grant No. 91016028 and the Innovative Sustentation Fund for Excellent Ph.D. Students in NUDT under Grant No. B140101. Sincere thanks to Allen from the University of Utah for his kind help with applying VisIt.
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Published In
Journal of Aerospace Engineering
Volume 28 • Issue 1 • January 2015
Copyright
© 2014 American Society of Civil Engineers.
History
Received: Jan 31, 2013
Accepted: Jul 31, 2013
Published online: Aug 2, 2013
Discussion open until: Nov 3, 2014
Published in print: Jan 1, 2015
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