Numerical study on detonation initiation by shock wave via over-expansion in a supersonic premixed flow
- Paper number
IAC-14,C4,P,48,x26545
- Author
Dr. Yu Liu, Science and Technology on Scramjet Laboratory, National University of Defense Technology, China
- Coauthor
Prof. Jin Zhou, Science and Technology on Scramjet Laboratory, National University of Defense Technology, China
- Coauthor
Dr. Zhiyong Lin, Science and Technology on Scramjet Laboratory, National University of Defense Technology, China
- Year
2014
- Abstract
In this paper,detonation initiation by shock wave via over-expansion in a supersonic premixed flow is numerically investigated. The results confirm the possibility of this absolutely new method of detonation initiation in a supersonic flow, which is much simpler and less disturbing to the flow field than traditional methods, including initiation through a hot jet and through a wedge. Some involved problems in this method are also revealed, such as formation of aerodynamic wedge by boundary layer separation, dependence of overdriven degree of detonation on the back pressure, the characteristics of flow field behind the detonation wave, etc. To resolve these problems, the Spalart-Allmaras turbulence model and mesh adaption module is applied in the CFD code. This work is very meaningful and instructive for experiments about detonation in supersonic wind tunnels and thus for future application of detonation wave engine in supersonic and hypersonic flights.
- Abstract document
- Manuscript document
IAC-14,C4,P,48,x26545.pdf (🔒 authorized access only).
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