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Coupled Rolling and Pitching Oscillation Effects on Transonic Shock-Induced Vortex-Breakdown Flow of a Delta WingUnsteady, transonic vortex dominated flow over a 65 deg. sharp edged, cropped-delta wing of zero thickness undergoing forced coupled pitching and rolling oscillations is investigated computationally. The wing mean angle of attack is 20 deg. and the free stream Mach number and Reynolds number are 0.85 and 3.23 x 10(exp 6), respectively. The initial condition of the flow is characterized by a transverse terminating shock and vortex breakdown of the leading edge vortex cores. 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 the maximum pitch and roll amplitude is kept constant at 4.0 deg. Four cases demonstrate the following: simultaneous motion at a frequency of 1(pi), motion with a 90 deg. phase lead in pitch, motion with a rolling frequency of twice the pitching frequency, and simultaneous motion at a frequency of 2(pi). Comparisons with single mode motion at these frequencies complete this study and illustrate the effects of coupling the oscillations.
Document ID
19960020976
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
Report/Patent Number
AIAA Paper 96-0828
Meeting Information
34th Aerospace Sciences Meeting and Exhibit(Reno, NV)
Distribution Limits
Public
Copyright
Public Use Permitted.
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