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      Compounding Transient Airfoil Motions and the Effectiveness of Linear Superposition

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          Abstract

          This paper investigates, for the first time, the effects of compounding transient airfoil motions and the predictive capability of the linear superposition principle in vortex dominated flows. Significant increases in the peak lift and nose-down pitching moment were observed during the second of two transient plunging motions at a poststall angle of attack. The load response of the second motion was estimated through linear superposition of the first motion response with a surprising level of accuracy. Flowfield measurements revealed this performance to coincide with a constructive merging of leading-edge vortices (LEVs). LEV merging showed sensitivity to motion timing. Breakdown of the linear superposition prediction coincided with LEV detachment and trailing-edge vortex formation, which disrupted constructive LEV merging. The amplitude of the second motion showed no discernible effect on LEV merging, and subsequently the accuracy of the linear superposition prediction. An extension to periodic motion was investigated, where linear superposition of a single sinusoidal cycle was compared with the true periodic response. This was found to capture the mean lift increase for low to moderate reduced frequencies. Lift amplitude, however, was captured with reasonable accuracy across the range of reduced frequencies and amplitudes tested.

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          Leading-Edge Vortices: Mechanics and Modeling

          The leading-edge vortex (LEV) is known to produce transient high lift in a wide variety of circumstances. The underlying physics of LEV formation, growth, and shedding are explored for a set of canonical wing motions including wing translation, rotation, and pitching. A review of the literature reveals that, while there are many similarities in the LEV physics of these motions, the resulting force histories can be dramatically different. In two-dimensional motions (translation and pitch), the LEV sheds soon after its formation; lift drops as the LEV moves away from the wing. Wing rotation, in contrast, incites a spanwise flow that, through Coriolis tilting, balances the streamwise vorticity fluxes to produce an LEV that remains attached to much of the wing and thus sustains high lift. The state of the art of vortex-based modeling to capture both the flow field and corresponding forces of these motions is reviewed, including closure conditions at the leading edge and approaches for data-driven strategies.
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            Estimation of uncertainty bounds for individual particle image velocimetry measurements from cross-correlation peak ratio

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              Experimental and Computational Investigation of Transverse Gust Encounters

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                Author and article information

                Contributors
                Journal
                aiaaj
                AIAA Journal
                AIAA Journal
                American Institute of Aeronautics and Astronautics
                1533-385X
                12 August 2022
                October 2022
                : 60
                : 10
                : 5768-5778
                Affiliations
                University of Bath , Bath, England BA2 7AY, United Kingdom
                Author notes
                [*]

                Lecturer, Department of Mechanical Engineering, Somerset; s.c.bull@ 123456bath.ac.uk (Corresponding Author).

                [†]

                Research Associate, Department of Mechanical Engineering, Somerset.

                [‡]

                Senior Lecturer, Department of Mechanical Engineering, Somerset.

                Article
                J061640 J061640
                10.2514/1.J061640
                0a2816a8-e168-44d9-a487-9af73e409dbe
                Copyright © 2022 by the authors. Published by the American Institute of Aeronautics and Astronautics, Inc., with permission. All requests for copying and permission to reprint should be submitted to CCC at www.copyright.com; employ the eISSN 1533-385X to initiate your request. See also AIAA Rights and Permissions www.aiaa.org/randp.
                History
                : 17 January 2022
                : 14 April 2022
                : 23 May 2022
                Page count
                Figures: 10, Tables: 0
                Funding
                Funded by: EPSRC grants (Engineering and Physical Sciences Research Council)
                Award ID: EP/M022307/1 EP/M000559/1
                Categories
                Regular Articles
                p2263, Fluid Dynamics
                p1804, Aerodynamics
                p1973, Vortex Dynamics
                p20543, Aerodynamic Performance
                p16684, Velocimetry
                p1975, Boundary Layers
                p1976, Flow Regimes
                p3749, Turbulence
                p2132, Aircraft Operations and Technology
                p1812, Airfoil

                Engineering,Physics,Mechanical engineering,Space Physics
                Freestream Velocity,Vortex Shedding,Lift Coefficient,Trailing Edges,Particle Image Velocimetry,Vorticity,Shear Layers,Selective Laser Sintering,Flow Conditions,NACA 0012

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