Flow structure on a three-dimensional wing subjected to small amplitude perturbations

Yilmaz, Turgut O.; Rockwell, D.

doi:10.1007/s00348-009-0637-2

Cited by 3 publications

(3 citation statements)

References 23 publications

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“…The plane passing through the centerbody of the 1303 UCAV model indicated in Fig. 1 represents, in essence, a plane of zero normal velocity, verified by dye visualization and PIV measurements, in comparison with a full wing configuration, as described in detail by Yilmaz and Rockwell [44]. For this wing arrangement within the aforementioned test section of the water channel, as shown in Fig.…”

Section: Experimental System and Techniquesmentioning

confidence: 65%

“…Thus, the establishment of the connectivity of the overall block-level system is fundamentally a two-part process; direct-injection donorreceiver pairs arising from the decomposition of the grids into blocks are identified, and the grid-level connectivity for the noncoincident Fig. 1 Overview of experimental system showing arrangement for particle image velocimetry system in relation to half-wing mounted in water channel, and definitions of parameters and zoomed-in views of half-wing in relation to full wing (from Yilmaz and Rockwell [44]). interpolation points established by the low-order connectivity software is transformed into the block-level system.…”

Section: E Overset Methodologymentioning

confidence: 99%

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1303 Unmanned Ccombat Air Vehicle Flowfield Simulations and Comparison with Experimental Data

Sherer¹,

Visbal²,

Gordnier³

et al. 2011

Journal of Aircraft

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In this work, high-order computations of the flowfield around a 1303 unmanned combat air vehicle configuration are performed and compared with recently collected experimental data obtained at Lehigh University. The computational approach used a high-order overset-grid flow solver developed in the Air Vehicles Directorate of the U.S. Air Force Research Laboratory that employs up-to-sixth-order compact finite differences and high-order, low-pass numerical filters to accurately resolve detailed flow features in a robust manner. The experimental data was collected via a particle image velocimetry technique in a free-surface water channel. Both quantitative and qualitative comparisons between computational and experimental results are done at a plane located at eight-tenths of the half-span for various Reynolds numbers and angles of attack, with the results comparing quite favorably for most flow conditions. Computational images of the flowfield are used to elucidate angle of attack and Reynolds number effects on this configuration, as well as to investigate the formation and evolution of the leading-edge and centerbody vortical structures and the impact that angle of attack has on their formation mechanisms. Nomenclature a, b = explicit compact differencing coefficients C root = wing root chord C = local wing chord at given spanwise locationviscous vector fluxes f i = explicit compact filter coefficients I = identity matrix I p , J p , K p = computational indices of interpolation donor point J = Jacobian of the coordinate transformation L mac = mean aerodynamic chord L ref = reference length (L ref L mac ) M = Mach number Pr = Prandtl number, 0.72 for air p = nondimensional static pressure Q = vector of dependent variables Re = reference Reynolds number, 1 u 1 L ref = 1 Re C root = reference Reynolds number based on wing root chord, 1 u 1 C root = 1 Re mac = reference Reynolds number based on mean aerodynamic chord, 1 u 1 L mac = 1 R , R , R = Laplace interpolation coefficients in , , and directions S = wing semispan T = nondimensional static temperature t = nondimensional time U, V, W = contravariant velocity components U 1 = freestream velocity u, v, w = nondimensional Cartesian velocity components in the x, y, and z directions u 1 , u 2 , u 3 = u, v, w hVi = time-averaged velocity vector x, y, z = nondimensional Cartesian coordinates in streamwise, normal, and spanwise directions based on wing orientation (nondimensionalized by the mean aerodynamic chord, L mac ) x LE = x coordinate of the local leading edge as measured from the apex x 1 , x 2 , x 3 = x, y, z x = nondimensional chordwise distance from the local leading edge, x x LE =C x root = nondimensional chordwise distance from the apex, x=C root = angle of attack f = implicit compact filter coefficient = implicit compact differencing coefficient = specific heat ratio, 1.4 for air , , = interpolation offsets in the , , and directions ij = Kronecker delta function 2 , 2 , 2 = second-order finite difference operators in , , 6 , 6 , 6 = sixth-order finite differe...

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Section: Experimental System and Techniquesmentioning

confidence: 65%

Section: E Overset Methodologymentioning

confidence: 99%

1303 Unmanned Ccombat Air Vehicle Flowfield Simulations and Comparison with Experimental Data

Sherer¹,

Visbal²,

Gordnier³

et al. 2011

Journal of Aircraft

View full text Add to dashboard Cite

show abstract

“…When active control is [40] used, vortex ring formations occur. Another application of perturbations on wings [42] prevents large-scale separation zone along the wing at high angle of attack. Flow characteristics of delta, diamond and lambda wings with stationary and perturbation conditions are investigated.…”

Section: Introductionmentioning

confidence: 99%

Investigation of Flow Characteristics and Vortex Formations of Lambda Wing at High Angles of Attack

Yavuz¹

2020

Journal of Thermal Engineering

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It is well known in literature that further stages of flow separation and vortex breakdown around wings can be able to cause stall of wings. These formations must be investigated carefully for new plane types. However, some limited studies are available, especially on lambda wing for high angles of attack. In this study, effect of angle of attack on flow characteristics and vortex breakdown around a lambda wing is investigated with a constant Reynolds number of 10000. Computational fluid dynamic analysis is used and results of high angles of attack of the wing are given up to 45 0 which are not available in literature. Open water channel simulation is used. Vortex breakdown initially begins at an angle of 17 0 and it almost reaches to tip of wing when angle of attack is equal to 25 0. Vortices get stronger at further increments of angle of attack and they become to nearly equal length of wing at 45 0. Rounding effect of leading edges is investigated for decreasing vortex magnitudes. Streamline, particle injection, iso-value of vortices and location of stagnation points are given, and they are discussed in detail.

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Stereoscopic Particle Image Velocimetry Flowfield Investigation of an Unmanned Combat Air Vehicle

Roosenboom¹,

Konrath²,

Schröder³

et al. 2012

Journal of Aircraft

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Flow structure on a three-dimensional wing subjected to small amplitude perturbations

Cited by 3 publications

References 23 publications

1303 Unmanned Ccombat Air Vehicle Flowfield Simulations and Comparison with Experimental Data

1303 Unmanned Ccombat Air Vehicle Flowfield Simulations and Comparison with Experimental Data

Investigation of Flow Characteristics and Vortex Formations of Lambda Wing at High Angles of Attack

Stereoscopic Particle Image Velocimetry Flowfield Investigation of an Unmanned Combat Air Vehicle

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