Analysis of Combustion Oscillations in Heterogeneous Systems.
Abstract
This analysis is aimed at the near-wall processes in an injected, axisymmetric, viscous flow. It is a part of an overall study of solid propellant rocket instability, in which cold flow simulation is evaluated as a tool to elucidate possible instability-driving mechanisms. One such prominent mechanism seems to be visco-acoustic coupling, as indicated by earlier detailed order of magnitude analysis. The major component of the overall study involves numerical simulation of the full set of coreflow equations of motion (nonsteady, axisymmetric) by a modified MacCormack integration technique. To clarify some of the physical interactions inherent in the various regimes of the flowfield, two (separate) singular perturbation analyses have been carried out. The head-end boundary regime, and the injected sidewall layer, both involve appreciable viscous dissipation, and hence are characterized by predominantly parabolic differential systems. The inverse square root of the injection Reynolds number serves as a small-perturbation quantity.
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1983
- Accession Number
- ADA144436
Entities
People
- M. Ben-reuven
- M. Summerfield