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 (pages 35-36).
Rights
© 2007 Nathan L. Mundis, All rights reserved.
Document Type
Thesis - Open Access
File Type
text
Language
English
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
Link to Catalog Record
Recommended Citation
Mundis, Nathan Lee, "Magnetohydrodynamic power generation in a scramjet using a post combustor generator" (2007). Masters Theses. 4596.
https://scholarsmine.mst.edu/masters_theses/4596