The DLR Flow Solver TAU - Status and Recent Algorithmic Developments

Langer, Stefan; Schwöppe, Axel; Kroll, Norbert

doi:10.2514/6.2014-0080

Cited by 36 publications

(16 citation statements)

References 29 publications

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“…Viscous-wall no-slip boundary condition is strongly imposed. A detailed discussion is offered in Kroll, Langer & Schwöppe (2014). Steady base-flow solutions are obtained using the backward Euler method with lower-upper symmetric Gauss-Seidel iterations and local time stepping.…”

Section: Numerical Approachmentioning

confidence: 99%

Global instability of wing shock-buffet onset

Timme

2020

J. Fluid Mech.

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Shock buffet on wings encountered in edge-of-the-envelope transonic flight remains an unresolved and disputed flow phenomenon, challenging both fundamental fluid mechanics and applied aircraft aerodynamics. The question of global instability leading to flow unsteadiness is addressed herein. It is shown for the first time that incipient threedimensional shock buffet is governed by the dynamics of a single unstable linear eigenmode with its spatial structure describing previously reported buffet cells. An inner-outer Krylov approach is proposed to solve the arising large-scale eigenvalue problem iteratively using shift-and-invert spectral transformation and sparse iterative linear solver. The established numerical strategy with an industrial flow solver means that a practical noncanonical test case at high-Re flow condition can be investigated. A modern wing design with publicly available geometry and experimental data for code validation is studied. The numerical findings can be exploited for routes to flow control and model reduction. †

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Section: Numerical Approachmentioning

confidence: 99%

Global instability of wing shock-buffet onset

Timme

2020

J. Fluid Mech.

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“…Additionally, these coefficients are calculated here for several angles of attack using the numerical code TAU. 15 The geometries of the capsules investigated in this work were defined by Airbus DS in Les Mureaux, France, as candidate shapes for the entry and return capsule of the sample return mission MarcoPolo-R, 16 which was previously proposed to ESA as a medium sized mission for launch in 2024. One of the requirements of the ballistic entry flight is to perform the descent and landing phase without using parachutes.…”

Section: Introductionmentioning

confidence: 99%

Free Flight Investigation of Atmospheric Entry Capsules in Low Subsonic Flow

Preci

Gülhan

2015

AIAA Atmospheric Flight Mechanics Conference

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The dynamic properties of candidate shapes for re-entry capsules are investigated in low subsonic flow. Capsule models are brought to hovering in the free vertical jet facility VMK. The motion is observed and recorded by optical means, enabling the measurement of the position and the attitude of the models during the flight. Data analysis allows for the determination of effective aerodynamic properties of the models. The force and moment coefficients are determined from the experiments and compared to results from numerical simulation. Additionally, the limit cycle and the pitch damping sum distribution over the angle of attack are assessed from experiments with different initial boundary conditions. The influence of the shape, the position of the center of gravity, and the shoulder radius on the stability are also investigated.

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“…12 The solution of the adjoint problem is the natural connection between the 13 linearisations of the residual and the considered objective functional. Con- 14 sequently, the adjoint system inherits all the potential inconsistencies lying 15 between the residual and the objective; either on the level of partial differen- 16 tial equations (PDE) when the continuous-adjoint problem is constructed in 17 a derive-then-discretise approach [14,15,25,28,26], or on the discrete level algebraic constraints (discretised governing equations) weighted by the cor-43 responding discrete-adjoint multipliers. Summation by parts, the discrete [5,7], Nielsen et al [20] have manually ensured primal-dual 57 equivalence throughout the iteration process of a linearised, unstructured 58 finite-volume Navier-Stokes method.…”

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confidence: 99%

An adjoint view on flux consistency and strong wall boundary conditions to the Navier–Stokes equations

Stück

2015

Journal of Computational Physics

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The DLR Flow Solver TAU - Status and Recent Algorithmic Developments

Cited by 36 publications

References 29 publications

Global instability of wing shock-buffet onset

Global instability of wing shock-buffet onset

Free Flight Investigation of Atmospheric Entry Capsules in Low Subsonic Flow

An adjoint view on flux consistency and strong wall boundary conditions to the Navier–Stokes equations

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