Project Title:

Finite Element Code for Combustion Analysis of Advanced Propulsion Systems

11.03-8122
Finite Element Code for Combustion Analysis of Advanced Propulsion Systems
Huntsville Sciences Corp.
3313 Bob Wallace Avenue, Suite 201
Huntsville
AL
35805
Lawrence W.
Spradley
(205-536-8122)
MSFC

Abstract:

An advanced computational tool will be developed for analysis and design of advanced
space propulsion systems by modelling the turbulent, finite-rate, reacting, two-phase
flow in thrust chambers. Start-up and shutdown transients will be modeled with the
time-accurate algorithm. Finite elements will be used with a flux-vector-split technique
to provide a characteristic-based, upwind, fully implicit solution. The solution
domain will include the subsonic, transonic, and supersonic nozzle flow and the exhaust
plume.
The Phase I code will developed for axially symmetric flow of a single-phase gas
with a finite-rate kinetics package for hydrogen and oxygen and a two-equation, turbulent,
kinetic-energy closure model. In Phase II, the code will be extended to three dimensions,
arbitrary kinetics, and multi-phase flow. The development will use an existing finite-element,
flux-corrected transport code as a point of departure. The resulting code will provide
a modern and efficient tool to analyze and to design or modify existing and future
space propulsion systems.

Potential Commercial Application:

Potential Commercial Applications:   Commercial supersonic airplane development could
use these computational codes to provide propulsion data, to reduce test costs, and
to verify experimental measurements and design changes.