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

Abstract

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.