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Prediction and control of slender-wing rockThe unsteady Euler equations and the Euler equations of rigid-body dynamics, both written in the moving frame of reference, are sequentially solved to simulate the limit-cycle rock motion of slender delta wings. The governing equations of the fluid flow and the dynamics of the present multidisciplinary problem are solved using an implicit, approximately-factored, central-difference-like, finite-volume scheme and a four-stage Runge-Kutta scheme, respectively. For the control of wing-rock motion, leading-edge flaps are forced to oscillate anti-symmetrically at prescribed frequency and amplitude, which are tuned in order to suppress the rock motion. Since the computational grid deforms due to the leading-edge flaps motion, the grid is dynamically deformed using the Navier-displacement equations. Computational applications cover locally-conical and three-dimensional solutions for the wing-rock simulation and its control.
Document ID
19930030334
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Kandil, Osama A.
(NASA Langley Research Center Hampton, VA, United States)
Salman, Ahmed A.
(Old Dominion Univ. Norfolk, VA, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1992
Publication Information
Publication: In: ICAS, Congress, 18th, Beijing, China, Sept. 20-25, 1992, Proceedings. Vol. 2 (A93-14151 03-01)
Publisher: American Institute of Aeronautics and Astronautics, Inc.
Subject Category
Aircraft Stability And Control
Accession Number
93A14331
Funding Number(s)
CONTRACT_GRANT: NAG1-648
Distribution Limits
Public
Copyright
Other

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