Masters Theses

Abstract

"A scramjet with a post combustor MHD generator is examined. A quasi-one-dimensional model is developed to calculate the flow path from tip to tail. The model includes losses due to combustion irreversibility, incomplete combustion, chemically reacting flow, friction, MHD losses, and nozzle plume modeling. Flight Mach number, magnetic field strength, gas conductivity, MHD load factor, and MHD generator expansion angle are all varied in order to assess their effects on MHD power generated and thrust lost in the engine. The trends produced through the above variations are summarized in a set of model-fit equations. It is concluded that a post combustor MHD generator is a viable means of power generation in a scramjet and its power output can be regulated by controlling the input variable cited above"--Abstract, page iii

Advisor(s)

Riggins, David W.

Committee Member(s)

Eversman, Walter
Peacher, Jerry

Department(s)

Mechanical and Aerospace Engineering

Degree Name

M.S. in Aerospace Engineering

Publisher

University of Missouri--Rolla

Publication Date

Fall 2007

Pagination

xi, 98 pages

Note about bibliography

Includes bibliographical references (leaves 35-36).

Rights

© 2007 Nathan L. Mundis, All rights reserved.

Document Type

Thesis - Open Access

File Type

text

Language

English

Library of Congress Subject Headings

Airplanes -- Scramjet engines
Combustion chambers -- Mathematical models
Hypersonic planes -- Mathematical models
Magnetohydrodynamic generators

Thesis Number

T 9283

Print OCLC #

234490944

Electronic OCLC #

213864690

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