High-Pressure Liquid-Propellant Rocket Engine Combustion Instability: Complex System, Uncertainty Quantification, and Reduced Basis Modeling
Abstract
Objective of this research is to predict near, and supercritical combustion and injection dynamics, using high-pressure equation of state and variable properties, and developing three-dimensional wave dynamics model. Scientists will use the expansion of the uncertainty quantification to address thermo-physical and chemical parameters at these high pressure conditions. The framework developed using reduced-basis, and stochastic modeling will be extended to predict combustion instabilities in liquid rocket engines.
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- Mar 23, 2016
- Source ID
- FA95501510033
Entities
People
- William A. Sirignano
Organizations
- Air Force Office of Scientific Research
- United States Air Force
- University of California, Irvine