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  • 11
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    Three-dimensional elliptic grid generation about fighter aircraft for zonal finite-difference computations (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An elliptic grid-generation method for finite-difference computations about complex aerodynamic configurations is developed. A zonal approach is used, which involves first making a coarse global grid filling the entire physical domain and then subdividing regions of that grid to make the individual zone grids. The details of the grid-generation method are presented along with results of the present application, a wing-body configuration based on the F-16 fighter aircraft.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 86-0429
    Format: text
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    NASA TECHNICAL REPORTS
  • 12
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    Elliptic generation of composite three-dimensional grids about realistic aircraft (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An elliptic method for generating composite grids about realistic aircraft is presented. A body-conforming grid is first generated about the entire aircraft by the solution of Poisson's differential equation. This grid has relatively coarse spacing, and it covers the entire physical domain. At boundary surfaces, cell size is controlled and cell skewness is nearly eliminated by inhomogeneous terms, which are found automatically by the program. Certain regions of the grid in which high gradients are expected, and which map into rectangular solids in the computational domain, are then designated for zonal refinement. Spacing in the zonal grids is reduced by adding points with a simple, algebraic scheme. Details of the grid generation method are presented along with results of the present application, a wing-body configuration based on the F-16 fighter aircraft.
    Keywords: AERONAUTICS (GENERAL)
    Type: NASA-TM-88240 , A-86165 , NAS 1.15:88240
    Format: application/pdf
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  • 13
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    Transonic solutions for a multielement airfoil using the full-potential equation (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: Transonic flow solutions are obtained over a multielement airfoil (augmentor-wing) using the full-potential equation. Solutions obtained for a subcritical case and a strong shock case show good quantitative agreement with experiment in regions not dominated by viscous effects. In those regions where viscous effects are dominant, the results are still in good qualitative agreement. For the strong shock case, Mach number and angle-of-attack corrections were necessary to match experimental coefficient of lift. Typical results from the transonic augmentor-wing Potential Code on the Cray-1S computer require about 10 sec of CPU time for a three-order-of-magnitude drop in the maximum residual. The speed with which solutions can be generated, and the associated low cost, will make this code a practical tool for the design aerodynamicist.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 84-0300
    Format: text
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  • 14
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    A computer program to generate two-dimensional grids about airfoils and other shapes by the use of Poisson's equation (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A method for generating two dimensional finite difference grids about airfoils and other shapes by the use of the Poisson differential equation is developed. The inhomogeneous terms are automatically chosen such that two important effects are imposed on the grid at both the inner and outer boundaries. The first effect is control of the spacing between mesh points along mesh lines intersecting the boundaries. The second effect is control of the angles with which mesh lines intersect the boundaries. A FORTRAN computer program has been written to use this method. A description of the program, a discussion of the control parameters, and a set of sample cases are included.
    Keywords: AERODYNAMICS
    Type: NASA-TM-81198 , A-8178
    Format: application/pdf
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  • 15
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    Simplified clustering of nonorthogonal grids generated by elliptic partial differential equations (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A simple clustering transformation is combined with the Thompson, Thames, and Mastin (TTM) method of generating computational grids to produce controlled mesh spacings. For various practical grids, the resulting hybrid scheme is easier to apply than the inhomogeneous clustering terms included in the TTM method for this purpose. The technique is illustrated in application to airfoil problems, and listings of a FORTRAN computer code for this usage are included.
    Keywords: NUMERICAL ANALYSIS
    Type: NASA-TM-73252 , A-6950
    Format: application/pdf
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  • 16
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    Computation of the steady viscous flow over a tri-element 'augmentor wing' airfoil (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The augmentor wing consists of a main airfoil with a slotted trailing edge for blowing, and two smaller aft airfoils which shroud the jet. This configuration has been modeled for numerical simulation by a novel discretization procedure which generates four separate grids: three surface-oriented airfoil grids and one outer free-stream grid. Grid lines and slopes are continuous across boundaries, so grid overlap at common boundaries provides boundary information without interpolation. A two-dimensional unsteady thin-layer Navier-Stokes code is used to calculate the flow for the no-blowing case at freestream Mach number = 0.7, Re = 12,600.000, and angles-of-incidence = 1.05 deg. Qualitative agreement with experimental data indicates the utility of this procedure in the analysis of multi-element configurations.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 82-0021 , Aerospace Sciences Meeting; Jan 11, 1982 - Jan 14, 1982; Orlando, FL
    Format: text
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  • 17
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    Grid generation by elliptic partial differential equations for a tri-element Augmentor-Wing airfoil (1982)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Two efforts to numerically simulate the flow about the Augmentor-Wing airfoil in the cruise configuration using the GRAPE elliptic partial differential equation grid generator algorithm are discussed. The Augmentor-Wing consists of a main airfoil with a slotted trailing edge for blowing and two smaller airfoils shrouding the blowing jet. The airfoil and the algorithm are described, and the application of GRAPE to an unsteady viscous flow simulation and a transonic full-potential approach is considered. The procedure involves dividing a complicated flow region into an arbitrary number of zones and ensuring continuity of grid lines, their slopes, and their point distributions across the zonal boundaries. The method for distributing the body-surface grid points is discussed.
    Keywords: AERODYNAMICS
    Type: Numerical grid generation; Symposium on Numerical Generation of Curvilinear Coordinate Systems and Their Use in the Numerical Solution of Partial Differential Equations; Apr 13, 1982 - Apr 16, 1982; Nashville, TN
    Format: text
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  • 18
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    Program Aids Specification Of Multiple-Block Grids (1993)
    In:  Other Sources
    Details
    Publication Date: 2019-07-12
    Description: 3DPREP computer program aids specification of multiple-block computational grids. Highly interactive graphical preprocessing program designed for use on powerful graphical scientific computer workstation. Divided into three main parts, each corresponding to principal graphical-and-alphanumerical display. Relieves user of some burden of collecting and formatting many data needed to specify blocks and grids, and prepares input data for NASA's 3DGRAPE grid-generating computer program.
    Keywords: MATHEMATICS AND INFORMATION SCIENCES
    Type: ARC-13082 , NASA Tech Briefs (ISSN 0145-319X); 17; 8; P. 26
    Format: text
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