Unsteady vortex-dominated flow around wings with oscillating leading-edge flapsUnsteady vortex-dominated flow around delta wings with oscillating leading-edge flaps represents an important classs of problems for supermaneuverability and flow control of advanced aircraft. The problem is solved using time accurate integration of the unsteady, compressible, thin-layer Navier-Stokes equations in conjunction with the unsteady, linearized, Navier-displacement equations. Starting with an initial configuration of the wing and its flaps, the Navier-Stokes equations are solved on an initial structured grid for the steady flow. The forced oscillation of the flaps is then applied, and the problem is solved accurately in time. The Navier-displacement equations are solved for the grid deformation and the Navier-Stokes equations are solved for the flowfield. Symmetric and anti-symmetric flaps oscillations are presented to study the effect of the flaps oscillation on the leading-edge vortical flow.
Document ID
19910034677
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Kandil, Osama A. (Old Dominion Univ. Norfolk, VA, United States)
Salman, Ahmed A. (Old Dominion University Norfolk, VA, United States)