Flow Structure on Diamond and Lambda Planforms: Trailing-Edge Region

Yanıktepe, Bülent; Rockwell, D.

doi:10.2514/1.7618

Cited by 32 publications

(11 citation statements)

References 25 publications

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“…Inlet turbulent intensity is approximately selected as 0.3%, which is commonly used in experimental studies [43][44]46]. Water properties are used at normal room conditions in the numerical analyses, have a density of 1.000 kg/m3 and a viscosity of 0.001003 kg/ms.…”

Section: Numerical Models Of the Channel And Wingmentioning

confidence: 99%

“…Its leading edges are chamfered with an angle of 30° and edges are not rounded. Free-stream flow velocity is determined as 60.1 mm/s based on a constant Reynolds number of 10000 and chord length of lambda wing with respect to the study [43][44]. The total length of the flow domain is as 29.5 chord length, C. Grid structure of lambda wing model is given in Figure 4.…”

Section: Numerical Models Of the Channel And Wingmentioning

confidence: 99%

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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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Section: Numerical Models Of the Channel And Wingmentioning

confidence: 99%

Section: Numerical Models Of the Channel And Wingmentioning

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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“…There are only a few studies available. For example, Yaniktepe and Rockwell (2005) performed experimental investigations on non-slender diamond and lambda type wings to analyze flow structures at the trailing edge zones. In both wings, vortical flow structures in the cross-flow planes of trailing edge change rapidly with angles of attack, Į when delta wings have high sweep angle, ȁ more than 40 degree.…”

Section: Fig 1 Types Of Vortex Bursting In a Tubementioning

confidence: 99%

Flow structures in end-view plane of slender delta wing

et al. 2017

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Abstract. Present investigation focuses on unsteady flow structures in end-view planes at the trailing edge of delta wing, X/C=1.0, where consequences of vortex bursting and stall phenomena vary according to angles of attack over the range of 25° Į 35° and yaw angles, ȕ over the range of 0° ȕ 20°. Basic features of counter rotating vortices in end-view planes of delta win with 70° sweep angle, ȁ are examined both qualitatively and quantitatively using Rhodamine dye and the PIV system. In the light of present experiments it is seen that with increasing yaw angle, ȕ symmetrical flow structure is disrupted continuously. Dispersed wind-ward side leading edge vortices cover a large part of flow domain, on the other hand, lee-ward side leading edge vortices cover only a small portion of flow domain.

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“…Reviews of these investigations are provided by Gursul [14,15] and Gursul et al [16]. Experimental investigations on wings having various values of sweep angle in the low-to-moderate range, as well as on planar simplifications of UCAV configurations, have been addressed experimentally by Ol and Gharib [17], Yavuz et al [18], and Yaniktepe and Rockwell [19,20]. Computations of the flow structure on delta wings of low sweep angle, with emphasis on lower values of Reynolds number, have been performed by Gordnier and Visbal [21] using a high-order, structured-grid, finite difference algorithm [22].…”

mentioning

confidence: 99%

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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Flow Structure on Diamond and Lambda Planforms: Trailing-Edge Region

Cited by 32 publications

References 25 publications

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

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

Flow structures in end-view plane of slender delta wing

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

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