Numerical investigations on the VFE-2 65-degree rounded leading edge delta wing using the unstructured DLR TAU-Code

Schütte, Andreas; Lüdeke, Heinrich

doi:10.1016/j.ast.2012.03.002

Cited by 17 publications

(10 citation statements)

References 11 publications

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“…Several publications [17,21,35] of the author are used for the validation of the numerical method and grid generation approach and provide the validation for the RANS solver DLR TAU to justify the present numerical approach.…”

Section: Discussionmentioning

confidence: 99%

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Numerical Investigations of Vortical Flow on Swept Wings with Round Leading Edges

Schütte

2017

Journal of Aircraft

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The present work is investigating the vortex-dominated flow physics as well as the aerodynamic behavior of swept wing configurations with round leading edges. The research is based on numerical simulations using the computational fluid dynamics method DLR TAU. The target configurations are swept wings of constant aspect ratio, variable leading-edge contours, and leading-edge sweep angles. The work deals with the onset of the vortical flow at the leading edge for constant and variable leading-edge nose radii, the influence of the angle of attack, the leading-edge sweep, and the onflow Mach number. Furthermore, the aerodynamic behavior is analyzed and assessed, as well as the specific flow physics in the vicinity of the vortical flow separation at round leading edges. The objective of the present work is to provide a contribution for the design and assessment of the physical characteristics of swept wing configurations. Furthermore, sensitivities will be given for the design process. In addition, the current investigation provides a deeper understanding of the separation onset process and the flow physics of swept wing configurations with round leading edges. Nomenclaturewing reference length, depth of the wing, m M ∞ = onflow Mach number, equal to a∕U ∞ p = pressure, N∕m 2 q ∞ = onflow dynamic pressure, N∕m 2 Re ∞ = Reynolds number, equal to U ∞ · c ref ∕ν r = radius at nose of the profile, m r N = nondimensional leading-edge contour radius, equal to r∕c ref s = wing semispan, m T = temperature, K t = time, s U ∞ = onflow velocity, m∕s u = local velocity within the flowfield, m∕s x, y, z = Cartesian coordinates, m y W = initial wall distance, distance of first grid point from wing surface, m y = nondimensional value to assess resolution of boundary-layer wall unit, equal to τ W ∕ρ p · y W ∕ν α = angle of attack, deg β = angle of sideslip, deg γ = circulation Δt = discrete time step, s Δx = discrete step in space, m μ = dynamic viscosity, Ns∕m 2 ν = kinematic viscosity, m 2 ∕s ρ = density, kg∕m 3 τ W = wall friction, N∕m 2 φ = wing sweep, deg k∂ρ∕∂tk = density residual, kg∕m 3 s Subscripts le = leading edge r = root ref = reference parameter ∞ = onflow condition

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Section: Discussionmentioning

confidence: 99%

“…A summary of all numerical results is given by Fritz and Cummings [16]. A summary of the numerical results using the CFD method TAU are given in Schütte and Lüdeke [17]. The results of the VFE-2 provide a first understanding of the complex vortical flow around a delta wing with round leading edges.…”

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confidence: 99%

Numerical Investigations of Vortical Flow on Swept Wings with Round Leading Edges

Schütte

2017

Journal of Aircraft

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“…The grid topology and parameters are taken from a best practice approach at DLR applied on several configurations like VFE-2 delta wing, X-31 configuration and the generic UCAV SACCON. 13,14,15 The surface of Grid I is resolved using a quadrilateral mesh, whereas the surface of Grid II is resolved using triangular elements. The near wall layer of Grid I, in which the boundary layer is present, is resolved by 30 layers using hexahedral elements.…”

Section: B Computational Gridmentioning

confidence: 99%

Numerical Investigation of the Aerodynamic Properties of a Flying Wing Configuration

Huber

Schütte

Rein

2012

30th AIAA Applied Aerodynamics Conference

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The numerical investigations of a generic UCAV configuration are presented. These investigations are part of the DLR internal project UCAV-2010. Compressible speed conditions are considered and presented. The DLR-F17E UCAV configuration is a flying lambda delta wing with sweep angle of 53° and varying leading edge radius. The flow field of this UCAV configuration is dominated by vortex structures and vortex-to-vortex interaction. The paper aims to give a comparison between numerical-and experimental investigations in order to gain a deeper understanding of the complex flow physics. Furthermore, it will highlight the influence of Mach-and Reynolds number change on the flow and the overall aerodynamic behavior of the configuration. The DLR TAU-Code is used to simulate the flow field, using an unstructured grid and the turbulence model of Spalart-Allmaras. Forces and moment measurements taken in the DNW-TWG, Göttingen, on the DLR-F17E configuration serve as the experimental basis to validate the numerical findings. Findings on the SACCON configuration serve as a comparison case aiming to show possible portability between different model scales but also to find analogies between low speed (M=0.15) and compressible speed (M=0.5) scenarios. This paper builds up upon the finding within the NATO/RTO AVT-161 Research Task Group on "Assessment and Control Predictions for NATO Air and Sea Vehicles" and its findings shall serve as a basis for further experimental investigations of medium to high speed wind tunnel experiments. Furthermore, this paper addresses the importance of understanding and the ability to predict controlled-and uncontrolled flow separation and the interaction of vortex systems in order to estimate the aerodynamic behavior within the entire flight envelope and to meet Stability-and Control needs.

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“…The agreement between the numerical results and the experimental data is mildly good, considering the quite coarse mesh and the simple turbulent model used. Note also that capturing the correct position of the vortices separation and reattachment points is quite challenging for this test case, as observed in other numerical simulations [36].…”

Section: Nasa Delta Wingmentioning

confidence: 55%

High-order linear and non-linear residual distribution schemes for turbulent compressible flows

Santis

2015

Computer Methods in Applied Mechanics and Engineering

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Numerical investigations on the VFE-2 65-degree rounded leading edge delta wing using the unstructured DLR TAU-Code

Cited by 17 publications

References 11 publications

Numerical Investigations of Vortical Flow on Swept Wings with Round Leading Edges

Numerical Investigations of Vortical Flow on Swept Wings with Round Leading Edges

Numerical Investigation of the Aerodynamic Properties of a Flying Wing Configuration

High-order linear and non-linear residual distribution schemes for turbulent compressible flows

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