Accession Number:

ADA370896

Title:

Computational Fluid Dynamics Analysis of a Dual Mode Thruster

Descriptive Note:

Master's thesis

Corporate Author:

NAVAL POSTGRADUATE SCHOOL MONTEREY CA

Personal Author(s):

• Williams, Adam N.

Report Date:

1999-09-01

Pagination or Media Count:

153.0

Abstract:

Current objectives at NASA Johnson Space Center ate directed at future upgrade and replacement of the U.S. Space Shuttles, currently toxic, Reaction Control System thrusters with dual mode thrusters that use nontoxic propellants. Experimentation to determine any performance advantages obtained using a dual mode thruster has not been performed by NASA. A computational fluid dynamics analysis is performed to evaluate the internal flow characteristics of this thruster under low thrust mode, torch igniter only, conditions. Several computational models, both two- and three-dimensional, are constructed to simulate the internal, steady-state flow characteristics. Comparison is made with current data on a similar type of flow highly underexpanded free-jet flow to show the appearance of barrel shocks and Mach disks. Regions of stagnate flow where heat transfer to chamber surfaces will be high and engine thrust performance are predicted based on computational data. Two different flow solvers, one using a finite volume method and the other using a finite difference method, are used to predict the engines performance. A comparison of the two flow solvers is given based on their relative performance to compute solutions to this problem.

Descriptors:

• *COMPUTATIONAL FLUID DYNAMICS
• *FINITE DIFFERENCE THEORY
• *THRUSTERS
• PERFORMANCE(ENGINEERING)
• THESES
• TURBULENCE
• SPACE SHUTTLES
• LIQUID PROPELLANT ROCKET ENGINES
• MACH NUMBER
• TWO DIMENSIONAL FLOW
• INVISCID FLOW
• DUAL MODE
• THRUST CONTROL
• REACTION CONTROL SYSTEMS
• STEADY FLOW
• STAGNATION POINT
• THREE DIMENSIONAL FLOW

Subject Categories:

• Fluid Mechanics
• Liquid Propellant Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE