Masters Theses
Abstract
“The present work numerically investigates the effect of surface roughness on flow separation over an airfoil. Two-dimensional NACA2412 airfoil and three- dimensional rectangular wing whose cross section is a NACA2412 are analyzed for surface roughness values of 180μm, 250μm and 400μm in 2D case and 250μm and 400μm in 3D case and the results are compared to those over a smooth surface. Simulations are done for angles of attack, which range between 0 and 20° at 3-degree interval at a Mach number of 0.25 using unstructured grid and Spalart-Allmaras model for turbulence. In the stall region the lift on the rough surface airfoil is observed to be more by 2-3% than the corresponding lift on the smooth surface airfoil. It is also observed that lift increases with an increase in surface roughness. It is also found that surface roughness delays flow separation by about 3-5%, delay being more on the surface of higher roughness”--Abstract, page iii.
Advisor(s)
Isaac, Kakkattukuzhy M.
Committee Member(s)
Finaish, Fathi
Insall, Matt
Department(s)
Mechanical and Aerospace Engineering
Degree Name
M.S. in Mechanical Engineering
Publisher
University of Missouri--Rolla
Publication Date
Summer 2001
Pagination
xii, 61 pages
Note about bibliography
Includes bibliographical references (pages 59-60).
Rights
© 2001 Harith Vadari, All rights reserved.
Document Type
Thesis - Restricted Access
File Type
text
Language
English
Thesis Number
T 7948
Print OCLC #
48269790
Link to Catalog Record
Electronic access to the full-text of this document is restricted to Missouri S&T users. Otherwise, request this publication directly from Missouri S&T Library or contact your local library.
http://merlin.lib.umsystem.edu/record=b4708279~S5Recommended Citation
Vadari, Harith, "Investigation of the effect of airfoil roughness for stall control" (2001). Masters Theses. 2073.
https://scholarsmine.mst.edu/masters_theses/2073
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