Anisotropic Hybrid Mesh Generation for Industrial RANS Applications

Martineau, David; Stokes, S.; Munday, S; Jackson, A.; Gribben, B.; Verhoeven, N.A.

doi:10.2514/6.2006-534

Cited by 52 publications

(20 citation statements)

References 7 publications

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“…Using the design cruising speed, the gust profiles and flight conditions for the cases simulated are listed in Table 1. These were run on an unstructured mesh, generated in SOLAR, 17 which consisted of a half-model of the wide-body aircraft and contained approximately 3 million points.…”

Section: Resultsmentioning

confidence: 99%

Aeroelastic Gust Response of an Aircraft Using a Prescribed Velocity Method in Viscous Flows

Huntley¹,

Jones²,

Gaitonde³

2017

23rd AIAA Computational Fluid Dynamics Conference

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General rightsThis document is made available in accordance with publisher policies. Please cite only the published version using the reference above. This paper presents the extension of the prescribed velocity method, known as the Split Velocity Method, for the purposes of modelling flexible aircraft gust responses. This is achieved by performing aeroelastic simulations using the computational fluid dynamics flow solver DLR-TAU coupled with a modal structural solver. This method is demonstrated by computing the response of a wide-body aircraft to a series of 1-cosine gusts. The results are compared to an existing prescribed velocity method, the Field Velocity Method. It is shown that the Field Velocity Method is a simplification of the Split Velocity Method and this results in noticeable differences in the solution for short wavelength gusts, where the velocity gradients are greatest.

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Section: Resultsmentioning

confidence: 99%

Aeroelastic Gust Response of an Aircraft Using a Prescribed Velocity Method in Viscous Flows

Huntley¹,

Jones²,

Gaitonde³

2017

23rd AIAA Computational Fluid Dynamics Conference

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“…12 A focus of the meshing process is laid on robustness, to ensure that meshes are generated for every possible combination of slat and flap setting. Further on a key aspect is the quality of the mesh, which should be independently of the high-lift setting.…”

Section: Iia Simulation Of the Aerodynamicsmentioning

confidence: 99%

Investigation on continuously deflectable High-Lift Devices for a 3D High-Lift Configuration

Franke

2015

33rd AIAA Applied Aerodynamics Conference

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This work deals with the investigation of continuously deflectable high-lift devices. The aim of this work is to derive optimal high-lift settings for off-design conditions and to evaluate the benefits of this technology. Off-design is related in this context to airport, aircraft and atmospheric specific conditions. Within the work a fully automatized process chain (high-fidelity methods are used) is implemented to generate an aerodynamic database for various high-lift settings. This data base is used by a preliminary design tool to simulate the overall aircraft for take-off, approach and landing at off-design. The resulting data are fed in a response surface model (RSM) to obtain the overall behavior for the slat/flap deflection angle domain. The interpolated values are used to derive optimal high-lift settings. The results show consistent behavior. It is found that for take-off valuable benefits can be achieved. For landing the results indicate that a further flap deflection than the standard landing setting is beneficial. NomenclatureAoA Aircraft angle of attack,MAC Mean aerodynamic chord length, [m] M Mach-number, [-] Re Reynolds-number, [-] S Reference area, [m 2 ] t Temperature, [ • C] T /W Thrust to weight ratio, [N/kg] T rev Reverse thrust, [N] v Velocity, [m/s] v s1g 1-g stall speed, [m/s] W Weight, [kg] W/S Wing-loading, [kg/m 2 ] AEO All engines operative BFL Balanced field length CAD Computer aided design CFD Computational fluid dynamics FAA Federal aviation administration ISA International standard atmosphere LFL Landing field length LW Landing weight MLW Maximum landing weight MTOW Maximum take-off weight OEI One engine inoperative OEW Operating empty weight RSM Response surface model TOFL Take-off field length TOW Take-off weight Symbols δ Deflection angle, [ • ] γ Flight path angle, [ • ] µ rGround roll friction coefficient, [-]

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“…The structured bottom-up philosophy, that is used in Pointwise to create a mesh, leads to a topologically complicated region at the wing nacelle intersection. Therefore the middle part of the wing together with the nacelle is meshed with the grid generator software Solar [16]. Solar is an unstructured grid generation software that discretizes surfaces with quadrilaterals and is capable to produce cells with a high aspect ratio.…”

Section: Mesh Generation Processmentioning

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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Anisotropic Hybrid Mesh Generation for Industrial RANS Applications

Cited by 52 publications

References 7 publications

Aeroelastic Gust Response of an Aircraft Using a Prescribed Velocity Method in Viscous Flows

Aeroelastic Gust Response of an Aircraft Using a Prescribed Velocity Method in Viscous Flows

Investigation on continuously deflectable High-Lift Devices for a 3D High-Lift Configuration

Propeller and Active High Lift Wing Interaction in Experiment and Simulation

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