Numerical studies of compressible flow over a double-delta wing at high angle of attack

Download
Author
Coutley, Raymond L.
Date
1990-03Advisor
Platzer, M. F.
Ekaterinaris, J.A.
Second Reader
Schiff, L. B.
Metadata
Show full item recordAbstract
The objective of this work is the investigation of vortical flows at high angles of attack using numerical techniques. The first step for a successful application of a numerical technique, such as fimite difference or finite volume, is the generation of a computational mesh which can capture adequately and accurately the important physics of the flow. Therefore, the first part of this work deals with the grid generation over a double-delta wing and the second part deals with the visualization of the computed flow field over the double-delta wing at different angles of attack. The surface geometry of the double-delta wing is defined algebraically. The developed surface grid generator provides flexibility in distributing the surface points along the axial and circumferential directions. The hyperbolic grid generation method is chosen for the field grid generation and both cylindrical and spherical grids are constructed. The computed low speed (M = 0.2) flow results at different angles of attack over the double-delta wing are visualized. Important flow characteristics of the leeward side flow field are discussed while the development of vortex interaction, occurrence and progression of vortex breakdown as the angle of attack increases is demonstrated. The computed results at different fixed angles of attack are presented.
Rights
This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.Collections
Related items
Showing items related by title, author, creator and subject.
-
Effect of juncture fillets on double-delta wings undergoing sideslip at high angles of attack
Chang, Wen-Huan (Monterey, California. Naval Postgraduate School, 1994-09);A flow visualization study of the vortical flow over a baseline double-delta wing model and a diamond-fillet double-delta wing model both with sharp leading edges was conducted in the Naval Postgraduate School water tunnel ... -
Effect of Forebody Strakes on Missile Asymmetric Vortices
Yuan, Chih-Chung; Howard, Richard M. (Aerospace Research Central (ARC), 1991);Wind-tunnel tests were conducted on a l/7th-scale vertically launched surface-to-air missile model to investigate the effects of forebody strakes on the side forces and yawing moments induced by nose-generate d asymmetric ... -
Lift enhancement of a wing/strake using pneumatic blowing.
Zgraggen, Craig J. (Monterey, California. Naval Postgraduate School, 1993-03);A low-speed wind-tunnel study to quantitatively measure the lift and drag effects of pneumatically controlling strake and leading-edge vortices generated by a half -span, genericfighter model was conducted. The study ...