Masters Theses

Title

A computational study of the flow fields around supersonic airfoils at low subsonic speeds

Abstract

"The sharp leading edge and mid-chord maximum thickness location of supersonic airfoils combine to create complex flow features at low speeds. Separation bubbles form at very low angles of attack and grow tremendously as incidence is increased further. These separated regions can have a large influence on the performance characteristics of the airfoil and are very sensitive to the ambient flow conditions. Recently, interest in supersonic business jets has promoted many questions regarding how to accurately model these complex flow physics. Four airfoil geometries have been selected for study, three of which are supersonic geometries"--Abstract, leaf iii.

Advisor(s)

Finaish, Fathi

Committee Member(s)

Riggins, David W.
Forrester, G.
Isaac, Kakkattukuzhy M.

Department(s)

Mechanical and Aerospace Engineering

Degree Name

M.S. in Aerospace Engineering

Publisher

University of Missouri--Rolla

Publication Date

Fall 2006

Pagination

xii, 103 leaves

Note about bibliography

Includes bibliographical references (page 47).

Rights

© 2006 Keith Edward Norton, All rights reserved.

Document Type

Thesis - Citation

File Type

text

Language

English

Library of Congress Subject Headings

Aerodynamics, Supersonic
Aerofoils
Numerical grid generation (Numerical analysis)
Turbulence -- Mathematical models

Thesis Number

T 9109

Print OCLC #

124114178

Link to Catalog Record

Full-text not available: Request this publication directly from Missouri S&T Library or contact your local library.

http://laurel.lso.missouri.edu/record=b5850890~S5

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