Grid generation for complex high-lift configurations

Rogers, Stuart E.; Cao, Hoa V.; Su, Tao

doi:10.2514/6.1998-3011

Cited by 37 publications

(9 citation statements)

References 16 publications

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“…Recent investigations have addressed more realistic high-lift geometries. For example, Rogers et al 14 applied and evaluated the overset grid method for a Boeing 747PD high-lift con guration.…”

Section: Introduction O Ne Current Challengefor Computational Uid Dynmentioning

confidence: 99%

Numerical Investigation of Slat and Compressibility Effects for a High-Lift Wing

Baker

Mathias

Roth

et al. 2002

Journal of Aircraft

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Three-dimensional multielement wings are simulated to investigate slat aerodynamics, numerical modeling techniques, and compressibility effects for high-lift ows. The computations are performed by solving both the incompressible and compressible Navier-Stokes equations on structured, overset grids. Turbulence is modeled via the one-equation Spalart-Allmaras model. All of the computed cases include the main wing with a half-span ap de ected to 40 deg. Three leading-edge con gurations of this unswept wing are then considered: no slat, full-span slat, and a three-quarter-span slat. The slat elements are deployed to 6 deg. Computations of the model, which simulates a landing con guration at 10-deg angle of attack and a chord-based Reynolds number of 3.7 £ £ 10 6 , are validated with surface pressure measurements acquired at the NASA Ames 7-by 10-Foot Wind Tunnel. By the observation of the changes to the high-lift ow eld by adding the slat, as well as by varying its spanwise length, a detailed computational assessment of a properly con gured slat is achieved. Moreover, the results increase the computational knowledge of how to model the slat ow physics accurately. For the three-element wing with partspan slat, modeling compressibility can have a large impact on the ow eld solution. Overall, compressibility is small, but it has signi cant global effects on the circulation and ow separation of each element.

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Section: Introduction O Ne Current Challengefor Computational Uid Dynmentioning

confidence: 99%

Numerical Investigation of Slat and Compressibility Effects for a High-Lift Wing

Baker

Mathias

Roth

et al. 2002

Journal of Aircraft

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“…Another methodology that lends itself to the solution of complicated flow problems is the overset, or chimera, structured grid method. The flow solver OVERFLOW is based on this approach and Rogers et al [79,80,68,70,69] have applied it to obtain flow simulations for several high-lift configurations including an early design version of the Boeing 747, a high wing transport with externally blown flaps, a simplified 3D high-lift wing, and a Boeing 777-200. Most impressive is their effort to reduce the time required to generate the surface and volume grids, to obtain the flow solution, and to post-process the data.…”

Section: Three-dimensional Methodsmentioning

confidence: 99%

The aerodynamic design of multi-element high-lift systems for transport airplanes

Dam¹

2002

Progress in Aerospace Sciences

254

109

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High-lift systems have a major influence on the sizing, economics, and safety of most transport airplane configurations. The combination of complexity in flow physics, geometry, and system support and actuation has historically led to a lengthy and experiment intensive development process. However, during the recent past engineering design has changed significantly as a result of rapid developments in computational hardware and software. In aerodynamic design, computational methods are slowly superseding empirical methods and design engineers are spending more and more time applying computational tools instead of conducting physical experiments to design and analyze aircraft including their high-lift systems. The purpose of this paper is to review recent developments in aerodynamic design and analysis methods for multi-element high-lift systems on transport airplanes. Attention is also paid to the associated mechanical and cost problems since a multi-element high-lift system must be as simple and economical as possible while meeting the required aerodynamic performance levels. r

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“…Since then this method is widely used in this field. It is now one of the most important grid techniques in the computational aerodynamics; for example, whole aircraft with wing and store [ Meakin , 1992], tiltrotor aircraft [ Meakin , 1993], Boeing 747 [ Cao et al , 1998; Rogers et al , 1998], space shuttle [ Buning et al , 1988], helicopter [ Duque et al , 1996], and others.…”

Section: Introductionmentioning

confidence: 99%

“Yin‐Yang grid”: An overset grid in spherical geometry

Kageyama

Sato

2004

Geochem Geophys Geosyst

339

238

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[1] A new kind of overset grid, named Yin-Yang grid, for spherical geometry is proposed. The Yin-Yang grid is composed of two identical component grids that are combined in a complemental way to cover a spherical surface with partial overlap on their boundaries. Each component grid is a low-latitude part of the latitude-longitude grid. Therefore the grid spacing is quasi-uniform, and the metric tensors are simple and analytically known. One can directly apply mathematical and numerical resources that have been written in the spherical polar coordinates or latitude-longitude grid. The complemental combination of the two identical component grids enables us to make efficient and concise programs. Simulation codes for geodynamo and mantle convection simulations using finite difference scheme based on the Yin-Yang grid are developed and tested. The Yin-Yang grid is suitable for massively parallel computers.

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Grid generation for complex high-lift configurations

Cited by 37 publications

References 16 publications

Numerical Investigation of Slat and Compressibility Effects for a High-Lift Wing

Numerical Investigation of Slat and Compressibility Effects for a High-Lift Wing

The aerodynamic design of multi-element high-lift systems for transport airplanes

“Yin‐Yang grid”: An overset grid in spherical geometry

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