Multi-Fidelity Modeling of Rocket Combustor Dynamics
Abstract
The goal of the project is to advance the state-of-the-art in reduced basis modeling with application in the context of Liquid Rocket Engines (LREs). To reliably predict the limit cycle amplitude and dominant modes of self-sustained pressure oscillations, as well as to assess the robustness and response of the system to imposed perturbations, the reduced model must overcome a number of challenges including geometric and physical.
Document Details
- Document Type
- DoD Grant Award
- Publication Date
- May 02, 2017
- Source ID
- FA95501710195
Entities
People
- Karthik Duraisamy
Organizations
- Air Force Office of Scientific Research
- United States Air Force
- University of Michigan