“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.
Isaac, Kakkattukuzhy M.
Mechanical and Aerospace Engineering
M.S. in Mechanical Engineering
University of Missouri--Rolla
xii, 61 pages
Note about bibliography
Includes bibliographical references (pages 59-60).
© 2001 Harith Vadari, All rights reserved.
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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~S5
Vadari, Harith, "Investigation of the effect of airfoil roughness for stall control" (2001). Masters Theses. 2073.
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