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Effects of Coupled Rolling and Pitching Oscillations on Transonic Shock-Induced Vortex-Breakdown Flow of a Delta WingUnsteady, transonic vortex-breakdown flow over a 65 deg. sharp edged, cropped-delta wing of zero thickness undergoing forced coupled pitching and rolling oscillations is investigated computationally. The initial condition of the flow is characterized by a transverse terminating shock which induces of the leading edge vortex cores to breakdown. The computational investigation uses the time-accurate solution of the laminar, unsteady, compressible, full Navier-Stokes equations with the implicit, upwind, Roe flux-difference splitting, finite-volume scheme. The main focus is to analyze the effects of coupled motion on the wing response and vortex-breakdown flow by varying oscillation frequency and phase angle while keeping the maximum pitch and roll amplitude equal.
Document ID
19960020977
Document Type
Conference Paper
Authors
Kandil, Osama A.
(Old Dominion Univ. Norfolk, VA United States)
Menzies, Margaret A.
(Old Dominion Univ. Norfolk, VA United States)
Date Acquired
August 17, 2013
Publication Date
February 1, 1996
Publication Information
Publication: Aeroelastic, CFD, and Dynamic Computation and Optimization for Buffet and Flutter Applications
Subject Category
Aerodynamics
Meeting Information
Meeting: 6th International Symposium on Computational Fluid Dynamics
Location: Lake Tahoe, NV
Country: United States
Start Date: September 4, 1995
End Date: September 8, 1995
Accession Number
96N24482
Distribution Limits
Public
Copyright
Public Use Permitted.
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