Title page for ETD etd-01082011-100759


Type of Document Master's Thesis
Author Tran, Kathleen
URN etd-01082011-100759
Title One Dimensional Analysis Program for Scramjet and Ramjet Flowpaths
Degree Master of Science
Department Mechanical Engineering
Advisory Committee
Advisor Name Title
O'Brien, Walter F. Jr. Committee Chair
Paul, Mark R. Committee Member
Schetz, Joseph A. Committee Member
Keywords
  • Hypersonic Propulsion
  • One Dimensional Modeling
  • Scramjets
  • Dual-Mode Scramjets
Date of Defense 2010-12-08
Availability unrestricted
Abstract
One-Dimensional modeling of dual mode scramjet and ramjet flowpaths is a

useful tool for scramjet conceptual design and wind tunnel testing. In this thesis,

modeling tools that enable detailed analysis of the flow physics within the combustor are

developed as part of a new one-dimensional MATLAB-based model named VTMODEL.

VTMODEL divides a ramjet or scramjet flow path into four major components: inlet,

isolator, combustor, and nozzle. The inlet module provides two options for supersonic

inlet one-dimensional calculations; a correlation from MIL Spec 5007D, and a kinetic

energy efficiency correlation. The kinetic energy efficiency correlation also enables the

user to account for inlet heat transfer using a total temperature term in the equation for

pressure recovery. The isolator model also provides two options for calculating the

pressure rise and the isolator shock train. The first model is a combined Fanno flow and

oblique shock system. The second model is a rectangular shock train correlation. The

combustor module has two options for the user in regards to combustion calculations.

The first option is an equilibrium calculation with a “growing combustion sphere”

combustion efficiency model, which can be used with any fuel. The second option is a

non-equilibrium reduced-order hydrogen calculation which involves a mixing correlation

based on Mach number and distance from the fuel injectors. This model is only usable for

analysis of combustion with hydrogen fuel. Using the combustion reaction models, the

combustor flow model calculates changes in Mach number and flow properties due to the

combustion process and area change, using an influence coefficient method. This method

iii

also can take into account heat transfer, change in specific heat ratio, change in enthalpy,

and other thermodynamic properties.

The thesis provides a description of the flow models that were assembled to create

VTMODEL. In calculated examples, flow predictions from VTMODEL were compared

with experimental data obtained in the University of Virginia supersonic combustion

wind tunnel, and with reported results from the scramjet models SSCREAM and RJPA.

Results compared well with the experiment and models, and showed the capabilities

provided by VTMODEL.

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