Computational Simulation of Flow Over a High Lift Trapezoidal Wing

Khare, Abhishek; Baig, Raashid; Ranjan, Rajesh; Shah, Stimit; Pavithran,; Nikam, Kishor; Moitra, Anutosh

doi:10.1260/175722509790291572

Cited by 6 publications

(5 citation statements)

References 2 publications

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“…A previous phase of the collaborative project had addressed basic CFD issues using a simplified high-lift configuration, the NASA Trapezoidal Wing -a generic high-lift wing with leading and trailing-edge devices 6 . Results from this previous phase were documented by Khare, et al 7 The current phase builds on process P improvements developed in the previous phase and extends them to a real-world airplane configuration based on Boeing's 777 airplane model. Recent advances in CFD solver technologies as well as high-performance computing platforms have provided feasible means for addressing the challenges of computing high-lift flow-fields.…”

Section: Introductionmentioning

confidence: 97%

Viscous Flow Analysis of a Twin-engine Commercial Transport Aircraft in High Lift Landing Configuration

Moitra

Ranjan

Khare

et al. 2011

29th AIAA Applied Aerodynamics Conference

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Extensive unstructured-grid CFD analysis has been performed for predicting performance of a twin-engine commercial transport airplane in landing configuration. The objective of the work was to identify and resolve complex gridding and solver related issues relevant to accurate prediction of complex flow physics associated with airplane high-lift systems. A variety of grid generation and CFD solution techniques were investigated for their efficacy in predicting performance of a complete airplane including high-lift devices e.g., multiple flaps and slats, and nacelle chines. Both steady and unsteady Reynolds Averaged Navier-Stokes (RANS) solution techniques were utilized. The role of relevant flowphysics phenomena in attainment of maximum lift as well as computational requirements for adequately modeling these phenomena were investigated. Computed aerodynamic forces are compared with available wind-tunnel test data.

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Section: Introductionmentioning

confidence: 97%

Viscous Flow Analysis of a Twin-engine Commercial Transport Aircraft in High Lift Landing Configuration

Moitra

Ranjan

Khare

et al. 2011

29th AIAA Applied Aerodynamics Conference

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“…The computations normally include a comprehensive code, coupled to Euler or Navier-Stockes solvers. The examples for a successful application of CFD are the codes FLUENT, OVERFLOW of NASA, FLOWer and TAU of Deutshes Zentrum für Luft und Raumfahr [4], [6], elsA and WAVES of ONERA [7], CFD++ [8], Star-CCM+ [9], [10], TAS of Takoku University and UPACS of Japan Institute of Space Technology and Aeronautics [11,12].…”

Section: Introductionmentioning

confidence: 99%

“…Some other advantages of structured mesh are better convergence and higher resolution. The unstructured mesh is identified by irregular connectivity, [8], [13]. It cannot easily be expressed as a two-dimensional or three-dimensional array.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic characteristics of airfoil with single plain flap for light airplane wing

Todorov

2015

International Conference on Military Technologies (ICMT) 2015

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A numerical study was performed on a NACA 23012 airfoil with a single plain flap to examine the aerodynamic coefficients at Reynolds number of 3×10 6 , and to help for identifying the forces acting on a light airplane wing. Besides, in the paper the flow fields around the airfoil with single plain flap were shown. All calculations were made using a CFD code. For a turbulent model the Spalart-Allmaras method was chosen. Conclusions were made about the aerodynamic efficiency of the proposed configuration wing-single plain flap.

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“…On the other hand, to reduce the wind-tunnel test costs and the design cycle time, some significant efforts are now underway with the development of computational fluid dynamics (CFD) techniques for the prediction of high-lift flowfields [3][4][5][6][7]. In this paper, emphasis is placed on the grid generation method.…”

Section: Introductionmentioning

confidence: 99%

“…Our goals are to modify the original octree Cartesian grid method through the use of an omni-tree data structure, so as to highlight the prominent changes in the grid generation of the numerical simulation of flowfield over high-lift configuration. In contrast to the previous studies that concentrate on a single solution approach, such as the multi-block grid method in [5], the chimera technique in [6], or the hybrid unstructured approach in [7], the present work offers the possibility of extending the applications and capabilities of the Cartesian grid method.…”

Section: Introductionmentioning

confidence: 99%

Comparison of Octree and Omni-Tree Cartesian Grid for Civil-Plane High-Lift Model Simulations

Sang

Shi

2013

Journal of Aircraft

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This comparative study is motivated by recent developments dealing with transport aircraft high-lift aerodynamics. Different than these developments Cartesian grids are used to achieve octree and omni-tree data structure. In this paper, the computation of complex flowfield is carried out using the cell-center finite volume method and dual-time stepping scheme. Based on the normal momentum equation a curvature-corrected symmetry technique has been developed to build the wall boundary treatment. A face-to-face algorithm is used in combination with the multizone technique, which can precisely establish the information exchange of flowfields in the interfaces among different zones. Compared with wind-tunnel experiments the above methods have been verified with two test cases involving, respectively, a takeoff configuration and a landing configuration. The focus is on the comparison of the octree and omni-tree data structure in Cartesian grid generation. The computed results indicate preliminarily that the omni-tree data structure is of higher efficiency, allows Cartesian grids to be adapted in an arbitrary manner, and offers the potential of a dramatic reduction of the total number of grids with the solution accuracy almost unaffected.

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Computational Simulation of Flow Over a High Lift Trapezoidal Wing

Cited by 6 publications

References 2 publications

Viscous Flow Analysis of a Twin-engine Commercial Transport Aircraft in High Lift Landing Configuration

Viscous Flow Analysis of a Twin-engine Commercial Transport Aircraft in High Lift Landing Configuration

Aerodynamic characteristics of airfoil with single plain flap for light airplane wing

Comparison of Octree and Omni-Tree Cartesian Grid for Civil-Plane High-Lift Model Simulations

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