Numerical Study of a Trapezoidal Wing High-Lift Configuration

Nash, Steven M.; Rogers, Stuart E.

doi:10.4271/1999-01-5559

Cited by 11 publications

(11 citation statements)

References 6 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…1). Although parts of the experimental data from two different wind tunnels have been used in previous studies [2][3][4][5][6], collectively, the data have never been officially published. This series of workshops was used as an opportunity to further evaluate and analyze some of the existing trap wing experimental data.…”

Section: Introductionmentioning

confidence: 98%

Summary of the First AIAA CFD High-Lift Prediction Workshop

Rumsey

Slotnick

Long

et al. 2011

Journal of Aircraft

181

View full text Add to dashboard Cite

The first AIAA CFD High-Lift Prediction Workshop was held in Chicago, Illinois, in June 2010. The goals of the workshop included an assessment of the numerical prediction capability of current-generation computational fluid dynamics (CFD) technology/codes for swept, medium/high-aspect-ratio wings in landing/takeoff (high-lift) configurations. Twenty-one participants from eight countries and 18 organizations submitted a total of 39 data sets of CFD results. A variety of grid systems (both structured and unstructured) were used. Trends due to flap angle were analyzed, and effects of grid family, grid density, solver, and turbulence model were addressed. Some participants also assessed the effects of support brackets used to attach the flap and slat to the main wing. This paper analyzes the combined results from all workshop participants. Comparisons with experimental data are made. A statistical summary of the CFD results is also included.

show abstract

Section: Introductionmentioning

confidence: 98%

Summary of the First AIAA CFD High-Lift Prediction Workshop

Rumsey

Slotnick

Long

et al. 2011

Journal of Aircraft

181

View full text Add to dashboard Cite

show abstract

“…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

View full text Add to dashboard Cite

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

show abstract

“…Validation studies have been conducted for a twodimensional configuration, a simplified three-dimensional configuration, and a realistic aircraft configuration. In NASA Langley, a series of simplified three-element trapezoidal high-lift wings with body pod have been tested and the experimental data are provided for validation and development of CFD methods for three-dimensional high-lift flows [4][5][6][7]. § In the Civil Transport Team of the Japan Aerospace Exploration Agency, wind-tunnel tests using a realistic aircraft takeoff and landing configuration deploying the high-lift devices with fuselage, nacelle-pylon and flap track fairing will be conducted to increase the knowledge of high-lift flows over a realistic aircraft configuration, to improve the measurement technologies, and to provide the detailed and systematic experimental data that can be disclosed for CFD validation from 2005 to 2006.…”

Section: Armentioning

confidence: 99%

Comparison of Reynolds-Averaged Navier-Stokes Simulations of Multi-Element High-Lift Configurations

Murayama

Imamura

Yamamoto

et al. 2007

Journal of Aircraft

View full text Add to dashboard Cite

In this study, flow computations are performed on three-dimensional high-lift configurations on multiblock structured and unstructured meshes with two turbulence models, Spalart-Allmaras model and Menter's shear stress transport model. Two kinds of three-element trapezoidal wings with full-span flap or part-span flap are computed. The objectives of this paper are to investigate the mesh dependency and the effect of turbulence models and improve the reliability in simulating the flow around high-lift devices. Importance of the mesh resolution to resolve the separated corner flows near the wing-fuselage junction is shown to improve the accuracy of computational results. It is also shown that the maximum lift and the angle at which it occurs are very sensitive to turbulence model and Menter's model gives better results at a higher angle of attack in the present computations. Nomenclature AR= aspect ratio of the wingsurface pressure coefficient c = mean aerodynamic chord e = Oswald efficiency factor M 1 = freestream Mach number Re = Reynolds number = angle of attack

show abstract

Numerical Study of a Trapezoidal Wing High-Lift Configuration

Cited by 11 publications

References 6 publications

Summary of the First AIAA CFD High-Lift Prediction Workshop

Summary of the First AIAA CFD High-Lift Prediction Workshop

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

Comparison of Reynolds-Averaged Navier-Stokes Simulations of Multi-Element High-Lift Configurations

Contact Info

Product

Resources

About