DID YOU KNOW? DTIC has over 3.5 million final reports on DoD funded research, development, test, and evaluation activities available to our registered users. Click
HERE to register or log in.
Accession Number:
ADA151999
Title:
Analysis of Combustion Oscillations in Heterogeneous Systems.
Descriptive Note:
Final rept. 15 Mar 82-15 Mar 84,
Corporate Author:
PRINCETON COMBUSTION RESEARCH LABS INC NJ
Report Date:
1984-05-01
Pagination or Media Count:
97.0
Abstract:
This study is aimed at elucidation of the physical mechanisms capable of driving acoustic instability in solid propellant rocket motors, of the type termed velocity-coupled instability. The first and second tasks of this research, Critical Literature Review, and Order of Magnitude Analyses of velocity-coupling mechanisms, have been reported earlier. The third part of the study, Analytical Simulation of the Interior Flowfield Within a Solid Propellant Grain, is reported herein. The subject of the present analysis is simulation of the cold-flow experiments by Dr. Brown at UTCCSD, in which nitrogen is injected through the porous sidewalls of a cylindrical pipe, creating an internal axisymmetric flow field. A comprehensive analytical model of the nonsteady flow processes entails a system of four partial differential equations for continuity, radial and axial momentum and thermal enthalpy. The flowfield is considered compressible and viscous, with all of the dissipative terms included. A focal point of the analysis has been the thin viscous sublayer adjacent to the porous surface, where visco-acoustic interactions occur. Additional keywords mathematical models combustion stability numerical analysis computations heat transfer and perturbations.
Distribution Statement:
APPROVED FOR PUBLIC RELEASE
