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
- Dual-Mode Scramjets
Date of Defense 2010-12-08 Availability unrestricted AbstractOne-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
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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