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

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.

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

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