Overview of the Hybrid RANS Code TAU

Gerhold, Thomas

doi:10.1007/3-540-32382-1_5

Cited by 255 publications

(76 citation statements)

References 3 publications

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“…The behavior of the fluid flow affecting the object of interest is simulated with the TAU-Code, a CFD tool developed by the DLR Institute of Aerodynamics and Flow Technology [20][21][22][23]. The TAUCode solves the compressible, 3-D, steady, or unsteady Reynoldsaveraged Navier-Stokes (URANS) equations using a finite volume formulation.…”

Section: A Computational Fluid Dynamics Solver Taumentioning

confidence: 99%

Flow Physics Analyses of a Generic Unmanned Combat Aerial Vehicle Configuration

Schütte

Hummel

Hitzel³

2012

Journal of Aircraft

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Within the NATO Research and Technology Organisation Applied Vehicle Technology (AVT)-161 task group, titled "Assessment of Stability and Control Predictions for NATO Air and Sea Vehicles," a 53° swept and twisted lambda wing with rounded leading edges is considered. In a first step, the symmetric flow conditions are analyzed in this paper in order to understand the corresponding flow physics. Experiments by the task group are used to develop proper numerical simulation tools for further applications in the design process of unmanned combat aerial vehicles as a part of future air-combat systems. The philosophy of the configuration under consideration is explained. The vortical flowfield is simulated using the DLR, German Aerospace Center TAU-Code applied with different turbulence models on various computational grids. Finally, a best practice is evaluated for medium and large angles of attack. A combination of these numerical results and experimental data lead to a proper understanding of the complex flow structure. Furthermore, this paper addresses the necessity for the predictability and understanding of controlled and uncontrolled flow separation, together with the interaction of the corresponding vortex systems in order to estimate stability and control issues for the entire flight envelope. NomenclatureA = attachment line C¿ = lift coefficient; ¿/(^oo • S) Cl = rolling moment coefficient; l/(q^ • S • c^f) Clß = rolling moment due to sideslip; 9C,/9Ĉ " = pitching moment coefficient (noseup positive); c" = yawing moment coefficient; «/(í/^, • 5-Cref) c"ß = yawing moment due to sideslip; 9C"/9Ĉ p = pressure coefficient; {p -/'oo)/9oo Cf = root chord length of the model cVef = reference length / = frequency /j = moment of inertia around x I y = moment of inertia around y k = reduced frequency; 27r • / • c,^f/VM = Mach number 9tx) = dynamic pressure coefficient; p^ • V^/2 R = Reynolds number; V^ • c^f/v S = reference area 5 = separation line s = half-span Presented a.s

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Section: A Computational Fluid Dynamics Solver Taumentioning

confidence: 99%

Flow Physics Analyses of a Generic Unmanned Combat Aerial Vehicle Configuration

Schütte

Hummel

Hitzel³

2012

Journal of Aircraft

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“…To test the feasibility of the experiments for code veri¦cations and for preliminary comparisons, 2D and 3D simulations with an even and an a priori de §ected panel were performed using the numerical §ow solver TAU [22,23]. The used grids are hybrid grids with semistructured layers close to surfaces and unstructured cells for the rest of the §ow domain.…”

Section: Numerical Simulation Of the Flow Fieldmentioning

confidence: 99%

Shock induced fluid-structure interaction on a flexible wall in supersonic turbulent flow

Willems

Gülhan

Esser

2013

Progress in Flight Physics

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Since escalating §uid structure interactions (FSI) can cause a complete loss of a spacecraft, a detailed knowledge of the mechanisms of §ow structure interactions in supersonic §ows is important for the design of future space transportation systems. The ¦rst step is to analyze the basic mechanisms at a generic test case that is ascertainable also with high quality simulations. Therefore, this work was devoted to the investigation of the shock wave boundary layer interaction on an elastic panel. During the wind tunnel experiments, the panel de §ection was measured with fast nonintrusive displacement sensors. On the §ow side pressure, high-speed Schlieren photography and oil-¦lm technique were used. The §ow manipulation due to the panel de §ection becomes manifest in a deformation of the impinging shock and the separation zone. The panel de §ection consists of a constant and a dynamic component. The experimental results are discussed and compared to numerical results.

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“…Tau is a software to solve the Reynolds-averaged-Navier-Stokes (RANS) equations. The development of Tau was started in the German CFD project MEGAFLOW [13] and is still under development by the C 2 A 2 S 2 E (Center for Computer Applications in Aerospace Science and Engineering) department of the DLR Institute of Aerodynamics and Flow Technol-ogy. In case of the simulation of the BNF w/t model a central finite volume scheme for the spatial discretization is used, whereas the discretization in the time domain is done by a Lower-Upper Symmetric-Gauss-Seidel (LUSGS) scheme.…”

Section: Methodsmentioning

confidence: 99%

Propeller and Active High Lift Wing Interaction in Experiment and Simulation

Lenfers¹,

Beck²,

Bauer

2016

Notes on Numerical Fluid Mechanics and Multidisciplinary Design

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Within the German BNF research project a generic twin-engine configuration with an active high-lift wing and modern turboprop engines is investigated. This paper deals with high fidelity RANS computations of the wind tunnel configuration measured in previous measurement campaigns. The simulation data is in good agreement with the experiment. The presented investigations focus on the jet flow due to the internally blown flap and the propeller slipstream.

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Overview of the Hybrid RANS Code TAU

Cited by 255 publications

References 3 publications

Flow Physics Analyses of a Generic Unmanned Combat Aerial Vehicle Configuration

Flow Physics Analyses of a Generic Unmanned Combat Aerial Vehicle Configuration

Shock induced fluid-structure interaction on a flexible wall in supersonic turbulent flow

Propeller and Active High Lift Wing Interaction in Experiment and Simulation

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