Investigation of the effect of airfoil roughness for stall control

Author

Harith Vadari

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.

Recommended Citation

Vadari, Harith, "Investigation of the effect of airfoil roughness for stall control" (2001). Masters Theses. 2073.
https://scholarsmine.mst.edu/masters_theses/2073