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A numerical study of the unsteady motion of a wing using N-body approximation
Published in American Institute of Aeronautics and Astronautics Inc.
2014
Abstract
Numerical simulation of unsteady motion of wing through undisturbed uid is formulated using Unsteady Vortex Lattice Method. Singularities in the form of vortex ring elements are distributed over the surface of the wing mean camber and remain fixed in space. The wake vortex ring singularities are free to deform under the action of velocity field induced by the combination of moving wing and deforming wake vortex ring elements. CL, CDi, γ distribution etc., are calculated for different cases of unsteady motion. A free-wake algorithm is developed based on the higher order numerical integration schemes. Minimum cut-off distance to avoid r-1 numerical singularity is obtained from Rankine vortex model. No-normal flow boundary condition is imposed over the surface of mean camber and the resulting MN × MN equations are solved for γ using LU decomposition.
About the journal
JournalData powered by Typeset52nd AIAA Aerospace Sciences Meeting - AIAA Science and Technology Forum and Exposition, SciTech 2014
PublisherData powered by TypesetAmerican Institute of Aeronautics and Astronautics Inc.
ISSN0001-1452
Impact Factor1.868
Open AccessNo
Citation Styleunsrt
Sherpa RoMEO Archiving PolicyGreen
Concepts (14)
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    Aerospace engineering
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    Cambers
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    Computational fluid dynamics
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    Velocity
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    Wakes
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    FLOW BOUNDARY CONDITIONS
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    Lu decomposition
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    NUMERICAL INTEGRATION SCHEME
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    RANKINE VORTICES
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    UNSTEADY MOTION
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    UNSTEADY VORTEX-LATTICE METHODS
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    Velocity field
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    VORTEX RINGS
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    Vortex flow