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  • 1
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    Algebraic grid generation about wing-fuselage bodies (1987)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: An algebraic procedure for generating boundary-fitted grids about wing-fuselage configurations is presented. A wing-fuselage configuration consists of two aircraft components specified by cross sections and mathematically represented by Coons' patches. Several grid blocks are constructed to cover the entire region surrounding the configuration, and each grid block maps into a computational cube. Grid points are first determined on the six boundary surfaces of a block and then in the interior. Grid points on the surface of the configuration are derived from the intersection of planes with the Coons' patch definition. Approximate arc length distributions along the resulting grid curves concentrate and disperse grid points. The two-boundary technique and transfinite interpolation are used to determine grid points on the remaining boundary surfaces and block interiors.
    Keywords: AERODYNAMICS
    Type: Journal of Aircraft (ISSN 0021-8669); 24; 868-872
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Surface definition and grid generation about an Assured Crew Return Vehicle (ACRV) for Space Station Freedom (1990)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: The surface definition and grid generation about an Assured Crew Return Vehicle (ACRV) for the Space Station Freedom are described. The purpose of the surface definition and grid generation is to provide the necessary geometry information for CFD calculations about the vehicle. There are two salient features in this description. The first is that the numerical model representing the ACRV configuration is obtained from the measurement of an existing wind tunnel model. The method for smoothing the measured data and obtaining the numerical model is described. The second feature is the description of the algebraic grid generation method and software to compute volume grids about the ACRV. The methods and software allow rapid computation of volume grids for a wide range of flow conditions.
    Keywords: AERODYNAMICS
    Type: Computing Systems in Engineering (ISSN 0956-0521); 1; 2-4,
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Algebraic grid generation for wing-fuselage bodies (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An algebraic procedure for the generation of boundary-fitted grids about wing-fuselage configurations is presented. A wing-fuselage configuration is specified by cross sections and mathematically represented by Coons' patches. A configuration is divided into sections so that several grid blocks that either adjoin each other or partially overlap each other can be generated, and each grid has six surfaces that map into a computational cube. Grids are first determined on the six boundary surfaces and then in the interior. Grid curves that are on the surface of the configuration are derived using plane-patch intersections, and single-valued functions relating approximate arc lengths along the curves to computational coordinates define the distribution of grid points. The two-boundary technique and transfinite interpolation are used to determine the boundary surface grids that are not on the configuration, and transfinite interpolation with linear blending functions is used to determine the interior grids.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 84-0002
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    A grid spacing control technique for algebraic grid generation methods (1982)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: A technique which controls the spacing of grid points in algebraically defined coordinate transformations is described. The technique is based on the generation of control functions which map a uniformly distributed computational grid onto parametric variables defining the physical grid. The control functions are smoothed cubic splines. Sets of control points are input for each coordinate directions to outline the control functions. Smoothed cubic spline functions are then generated to approximate the input data. The technique works best in an interactive graphics environment where control inputs and grid displays are nearly instantaneous. The technique is illustrated with the two-boundary grid generation algorithm.
    Keywords: NUMERICAL ANALYSIS
    Type: AIAA PAPER 82-0226 , Aerospace Sciences Meeting; Jan 11, 1982 - Jan 14, 1982; Orlando, FL
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Gridding strategies and associated results for winged entry vehicles (1991)
    In:  Other Sources
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    Publication Date: 2019-07-13
    Description: Two volume grid strategies based on similar software are presented for a geometrically complex entry vehicle. It is shown that quick relatively simple grid generation techniques can be used to construct computational grids about entry vehicles with nontrivial geometric complexity. Particular attention is given to both single- and dual-block grid topologies for a lifting body and solution generated on each grid. Results indicate that the grid topology can have an effect on the nature of the solution.
    Keywords: NUMERICAL ANALYSIS
    Type: International Conference on Numerical Grid Generation in Computational Fluid Dynamics and Related Fields; Jun 03, 1991 - Jun 07, 1991; Barcelona; Spain
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Grid generation and compressible flow computations about a high-speed civil transport configuration (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Techniques and software are discussed for generating grids about a high-speed civil transport configuration. The configuration is defined by a computer-aided design system in wing, fuselage, tail and engine-nacelle components. Grid topology and the surfaces outlining the blocks of the topology are computed with interactive software. The volume grid is computed using software based on transfinite interpolation and Lagrangian blending functions. Several volume grids for inviscid and viscous flow have been generated using this system of codes. Demonstration flowfields around this vehicle are described.
    Keywords: NUMERICAL ANALYSIS
    Type: International Conference on Numerical Grid Generation in Computational Fluid Dynamics and Related Fields; Jun 03, 1991 - Jun 07, 1991; Barcelona; Spain
    Format: text
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    NASA TECHNICAL REPORTS
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