A computational study of the flow fields around supersonic airfoils at low subsonic speeds
"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.
Riggins, David W.
Isaac, Kakkattukuzhy M.
Mechanical and Aerospace Engineering
M.S. in Aerospace Engineering
University of Missouri--Rolla
xii, 103 leaves
© 2006 Keith Edward Norton, All rights reserved.
Thesis - Citation
Library of Congress Subject Headings
Numerical grid generation (Numerical analysis)
Turbulence -- Mathematical models
Print OCLC #
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
Norton, Keith Edward, "A computational study of the flow fields around supersonic airfoils at low subsonic speeds" (2006). Masters Theses. 5899.