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  • 1
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    Streaming potential in porous media: 2. Theory and application to geothermal systems (1999)
    American Geophysical Union
    Details
    Publication Date: 1999-09-10
    Print ISSN: 0148-0227
    Electronic ISSN: 2156-2202
    Topics: Geosciences
    Published by American Geophysical Union
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    PAPER CURRENT
  • 2
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    The CMC/3DPNS computer program for prediction of three-dimension, subsonic, turbulent aerodynamic juncture region flow. Volume 2: Users' manual (1982)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The CMC fluid mechanics program system was developed to transmit the theoretical solution of finite element numerical solution methodology, applied to nonlinear field problems into a versatile computer code for comprehensive flow field analysis. Data procedures for the CMC 3 dimensional Parabolic Navier-Stokes (PNS) algorithm are presented. General data procedures a juncture corner flow standard test case data deck is described. A listing of the data deck and an explanation of grid generation methodology are presented. Tabulations of all commands and variables available to the user are described. These are in alphabetical order with cross reference numbers which refer to storage addresses.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-165997 , NAS 1.26:165997 , CMC/82TR-2.2-VOL-2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Three-Dimensional, Subsonic, Turbulent Juncture Region Flow (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: CMC3DPNS predicts three-dimensional, subsonic, turbulent aerodynamic juncture region flow. Versatile program for comprehensive flow-field analysis applies finite-element methodology to nonlinear field problems. Order-ofmagnitude analysis of subsonic, three-dimensional, steady time-averaged NavierStokes equations for semibounded aerodynamic juncture geometries yields para bolic Navier-Stokes equations. CMC3DPNS solves these equations to predict juncture-region flow.
    Keywords: MECHANICS
    Type: LAR-13263 , NASA Tech Briefs (ISSN 0145-319X); 9; 4; P. 150
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Finite element analysis of aeroacoustic jet-flap flows (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A computational analysis was performed on the steady, turbulent aerodynamic flowfields associated with a jet-blown flap. For regions devoid of flow separation, a parabolic approximation to the governing time-averaged Navier-Stokes equations was applied. Numerical results are presented for the symmetry plane flow of a slot-nozzle planar jet flap geometry, including prediction of flowfield evolution within the secondary mixing region immediately downstream of the trailing edge. Using a two equation turbulence kinetic energy closure model, rapid generation and decay of large spatial gradients in mean and correlated fluctuating velocity components within the immediate wake region were predicted. Modifications to the turbulent flow structure, as induced by porous surface treatment of the flap, were evaluated. The recirculating flow within a representative discrete slot in the surface was evaluated, using the two dimensional, time-averaged Navier-Stokes equations.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-2931 , COMOC-76TR-1.2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    The finite element method in low speed aerodynamics (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The finite element procedure is shown to be of significant impact in design of the 'computational wind tunnel' for low speed aerodynamics. The uniformity of the mathematical differential equation description, for viscous and/or inviscid, multi-dimensional subsonic flows about practical aerodynamic system configurations, is utilized to establish the general form of the finite element algorithm. Numerical results for inviscid flow analysis, as well as viscous boundary layer, parabolic, and full Navier Stokes flow descriptions verify the capabilities and overall versatility of the fundamental algorithm for aerodynamics. The proven mathematical basis, coupled with the distinct user-orientation features of the computer program embodiment, indicate near-term evolution of a highly useful analytical design tool to support computational configuration studies in low speed aerodynamics.
    Keywords: AERODYNAMICS
    Type: NASA-CR-143190 , TR-75-T5
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Finite element analysis of low speed viscous and inviscid aerodynamic flows (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A weak interaction solution algorithm was established for aerodynamic flow about an isolated airfoil. Finite element numerical methodology was applied to solution of each of differential equations governing potential flow, and viscous and turbulent boundary layer and wake flow downstream of the sharp trailing edge. The algorithm accounts for computed viscous displacement effects on the potential flow. Closure for turbulence was accomplished using both first and second order models. The COMOC finite element fluid mechanics computer program was modified to solve the identified equation systems for two dimensional flows. A numerical program was completed to determine factors affecting solution accuracy, convergence and stability for the combined potential, boundary layer, and parabolic Navier-Stokes equation systems. Good accuracy and convergence are demonstrated. Each solution is obtained within the identical finite element framework of COMOC.
    Keywords: AERODYNAMICS
    Type: NASA-CR-2908 , COMOC-77TR-2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Grid and metric generation on the assembly of locally bi-quadratic coordinate transformations (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The generation of metric coefficients of the coordinate transformation from a generally curved-sided domain boundary to the unit square (cube) is required for efficient solution algorithms in computational fluid mechanics. An algebraic procedure is presented for establishment of these data on the union of arbitrarily selected sub-domains of the global solution domain. A uniformly smooth progression of grid refinement is readily generated, including multiple specification of refined grids for a given macro-element domain discretization. The procedure is illustrated as generally applicable to non-simply connected domains in two and three dimensions.
    Keywords: NUMERICAL ANALYSIS
    Type: NASA. Langley Research Center Numerical Grid Generation Tech.; p 175-180
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    On recent advances and future research directions for computational fluid dynamics (1986)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: This paper highlights some recent accomplishments regarding CFD numerical algorithm constructions for generation of discrete approximate solutions to classes of Reynolds-averaged Navier-Stokes equations. Following an overview of turbulent closure modeling, and development of appropriate conservation law systems, a Taylor weak-statement semi-discrete approximate solution algorithm is developed. Various forms for completion to the final linear algebra statement are cited, as are a range of candidate numerical linear algebra solution procedures. This development sequence emphasizes the key building blocks of a CFD RNS algorithm, including solution trial and test spaces, integration procedure and added numerical stability mechanisms. A range of numerical results are discussed focusing on key topics guiding future research directions.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    An interaction solution algorithm for viscous aerodynamic performance prediction (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A weak-interaction solution algorithm is established for aerodynamic flow field prediction about an isolated airfoil. It requires numerical solution of differential equations governing potential flow, viscous and turbulent boundary layer flow, and the turbulent wake flow downstream of a trailing edge. The algorithm accounts for computed viscous displacement effects on the potential flow. These in turn alter the viscous flow through imposed pressure gradients. Closure for turbulence is accomplished using a second order model. Numerical evaluations assess factors affecting solution accuracy, convergence and stability for the combined potential, boundary layer, and parabolic Navier-Stokes equation systems as solved using a finite element algorithm.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 78-153 , Aerospace Sciences Meeting; Jan 16, 1978 - Jan 18, 1978; Huntsville, AL
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Finite element solution for energy conservation using a highly stable explicit integration algorithm (1972)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Theoretical derivation of a finite element solution algorithm for the transient energy conservation equation in multidimensional, stationary multi-media continua with irregular solution domain closure is considered. The complete finite element matrix forms for arbitrarily irregular discretizations are established, using natural coordinate function representations. The algorithm is embodied into a user-oriented computer program (COMOC) which obtains transient temperature distributions at the node points of the finite element discretization using a highly stable explicit integration procedure with automatic error control features. The finite element algorithm is shown to posses convergence with discretization for a transient sample problem. The condensed form for the specific heat element matrix is shown to be preferable to the consistent form. Computed results for diverse problems illustrate the versatility of COMOC, and easily prepared output subroutines are shown to allow quick engineering assessment of solution behavior.
    Keywords: MATHEMATICS
    Type: NASA-CR-130149 , REPT-9500-920257
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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