Masters Theses
Abstract
"A two-dimensional numerical study of the effects of a forward-facing supersonic air jet located at the stagnation point of a cylinder-wedge body on wave drag, heat transfer, and skin friction drag is presented for Mach 6.5 free stream flow at 30 km altitude. Jet exit area and jet Mach number are varied parametrically. The full Navier- Stokes equations are used with variable viscosity and variable thermal conductivity. The 2-D version of the FORTRAN code SPARK is used for all solutions. A detailed analysis of time and grid convergence is provided. It is shown that upstream injection can significantly modify the flow field. If the jet conditions are chosen properly, large reductions in drag and heat transfer can be obtained resulting in possible increases in the volumetric efficiency and static stability of aircraft as well as reductions in the heating protection requirements for hypersonic vehicles"--Abstract, page iv.
Advisor(s)
Nelson, Harlan F., 1938-2005
Committee Member(s)
Riggins, David W.
Isaac, Kakkattukuzhy M.
Bohner, Martin, 1966-
Department(s)
Mechanical and Aerospace Engineering
Degree Name
M.S. in Aerospace Engineering
Publisher
University of Missouri--Rolla
Publication Date
Spring 2000
Pagination
xi, 107 pages
Note about bibliography
Includes bibliographical references.
Rights
© 2000 Benjamin Michael Meyer, All rights reserved.
Document Type
Thesis - Restricted Access
File Type
text
Language
English
Thesis Number
T 7745
Print OCLC #
44645475
Electronic OCLC #
1108681635
Recommended Citation
Meyer, Benjamin Michael, "Numerical investigation of hypersonic drag and heat transfer using a forward facing jet" (2000). Masters Theses. 1926.
https://scholarsmine.mst.edu/masters_theses/1926
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Comments
This research has been partially funded by NASA NAG-1-2167 grant from the HYPER-X Program Office, C. R. McClinton, Technical Monitor, NASA Langley Research Center, Hampton, VA.