"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
Riggins, David W.
Mechanical and Aerospace Engineering
M.S. in Aerospace Engineering
University of Missouri--Rolla
xi, 98 pages
© 2007 Nathan L. Mundis, All rights reserved.
Thesis - Open Access
Library of Congress Subject Headings
Airplanes -- Scramjet engines
Combustion chambers -- Mathematical models
Hypersonic planes -- Mathematical models
Print OCLC #
Electronic OCLC #
Link to Catalog Recordhttp://laurel.lso.missouri.edu/record=b6430043~S5
Mundis, Nathan Lee, "Magnetohydrodynamic power generation in a scramjet using a post combustor generator" (2007). Masters Theses. 4596.