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  • 1
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    Implicit flux-split schemes for the Euler equations (1990)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA Journal (ISSN 0001-1452); 28; 973
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  • 2
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    Computation of laminar viscous-inviscid interactions in high-speed internal flows (1991)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: A review is given of computations for a series of nominally 2-D laminar viscous-inviscid interactions. Comparisons were made with detailed experimental shock tunnel results. The shock wave boundary layer interactions considered were induced by a compression ramp in one case and by an externally generated incident shock in the second case. In general, good agreement was reached between the grid refined calculations and experiment for the incipient and small separation conditions. For the highly separated flow, 3-D calculations which included the finite span effects of the experiment were required in order to obtain agreement with the data.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA, Lewis Research Center, Computational Fluid Dynamics Symposium on Aeropropulsion; p 473-486
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  • 3
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    Upwind relaxation algorithms for the Navier-Stokes equations (1987)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA Journal (ISSN 0001-1452); 25; 527-534
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  • 4
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    An implicit flux-split algorithm for the compressible Navier-Stokes equations (1987)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: An implicit upwind scheme for the compressible Navier-Stokes equations is described and applied to the internal flow in a dual-throat nozzle. The method is second-order accurate spatially and naturally dissipative. A spatially-split approximate factorization method is used to obtain efficient steady-state solutions on the NASA Langley VPS-32 (CYBER 205) supercomputer.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
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  • 5
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    A comparative study and validation of upwind and central-difference Navier-Stokes codes for high-speed flows (1988)
    In:  CASI
    Details
    Publication Date: 2017-10-02
    Description: A comparative study was made using 4 different computer codes for solving the compressible Navier-Stokes equations. Three different test problems were used, each of which has features typical of high speed internal flow problems of practical importance in the design and analysis of propulsion systems for advanced hypersonic vehicles. These problems are the supersonic flow between two walls, one of which contains a 10 deg compression ramp, the flow through a hypersonic inlet, and the flow in a 3-D corner formed by the intersection of two symmetric wedges. Three of the computer codes use similar recently developed implicit upwind differencing technology, while the fourth uses a well established explicit method. The computed results were compared with experimental data where available.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AGARD, Validation of Computational Fluid Dynamics. Volume 1: Symposium Papers and Round Table Discussion; 15 p
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  • 6
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    ICASE/LaRC Workshop on Adaptive Grid Methods (1995)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Solution-adaptive grid techniques are essential to the attainment of practical, user friendly, computational fluid dynamics (CFD) applications. In this three-day workshop, experts gathered together to describe state-of-the-art methods in solution-adaptive grid refinement, analysis, and implementation; to assess the current practice; and to discuss future needs and directions for research. This was accomplished through a series of invited and contributed papers. The workshop focused on a set of two-dimensional test cases designed by the organizers to aid in assessing the current state of development of adaptive grid technology. In addition, a panel of experts from universities, industry, and government research laboratories discussed their views of needs and future directions in this field.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CP-3316 , NAS 1.55:3316 , L-17539 , NIPS-96-07318 , Nov 07, 1994 - Nov 09, 1994; Hampton, VA; United States
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  • 7
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    Convergence of Defect-Correction and Multigrid Iterations for Inviscid Flows (2011)
    In:  CASI
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    Publication Date: 2019-07-13
    Description: Convergence of multigrid and defect-correction iterations is comprehensively studied within different incompressible and compressible inviscid regimes on high-density grids. Good smoothing properties of the defect-correction relaxation have been shown using both a modified Fourier analysis and a more general idealized-coarse-grid analysis. Single-grid defect correction alone has some slowly converging iterations on grids of medium density. The convergence is especially slow for near-sonic flows and for very low compressible Mach numbers. Additionally, the fast asymptotic convergence seen on medium density grids deteriorates on high-density grids. Certain downstream-boundary modes are very slowly damped on high-density grids. Multigrid scheme accelerates convergence of the slow defect-correction iterations to the extent determined by the coarse-grid correction. The two-level asymptotic convergence rates are stable and significantly below one in most of the regions but slow convergence is noted for near-sonic and very low-Mach compressible flows. Multigrid solver has been applied to the NACA 0012 airfoil and to different flow regimes, such as near-tangency and stagnation. Certain convergence difficulties have been encountered within stagnation regions. Nonetheless, for the airfoil flow, with a sharp trailing-edge, residuals were fast converging for a subcritical flow on a sequence of grids. For supercritical flow, residuals converged slower on some intermediate grids than on the finest grid or the two coarsest grids.
    Keywords: Aerodynamics
    Type: AIAA Paper 2011-3235 , NF1676L-11822 , 41st AIAA Fluid Dynamics Conference and Exhibit; Jun 27, 2011 - Jun 30, 2011; Honolulu, HI; United States
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  • 8
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    FUN3D Manual: 13.6 (2019)
    In:  CASI
    Details
    Publication Date: 2019-11-30
    Description: This manual describes the installation and execution of FUN3D version 13.6, including optional dependent packages. FUN3D is a suite of computational fluid dynamics simulation and design tools that uses mixed-element unstructured grids in a large number of formats, including structured multiblock and overset grid systems. A discretely-exact adjoint solver enables efficient gradient-based design and grid adaptation to reduce estimated discretization error. FUN3D is available with and without a reacting, real-gas capability. This generic gas option is available only for those persons that qualify for its beta release status.
    Keywords: Aerodynamics
    Type: NF1676L-34707 , NASA/TM-2019-220416
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  • 9
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    Textbook Multigrid Efficiency for Leading Edge Stagnation (2004)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A multigrid solver is defined as having textbook multigrid efficiency (TME) if the solutions to the governing system of equations are attained in a computational work which is a small (less than 10) multiple of the operation count in evaluating the discrete residuals. TME in solving the incompressible inviscid fluid equations is demonstrated for leading- edge stagnation flows. The contributions of this paper include (1) a special formulation of the boundary conditions near stagnation allowing convergence of the Newton iterations on coarse grids, (2) the boundary relaxation technique to facilitate relaxation and residual restriction near the boundaries, (3) a modified relaxation scheme to prevent initial error amplification, and (4) new general analysis techniques for multigrid solvers. Convergence of algebraic errors below the level of discretization errors is attained by a full multigrid (FMG) solver with one full approximation scheme (F.4S) cycle per grid. Asymptotic convergence rates of the F.4S cycles for the full system of flow equations are very fast, approaching those for scalar elliptic equations.
    Keywords: Aerodynamics
    Type: NASA/TM-2004-213037 , L-19023
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  • 10
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    Navier-Stokes Solutions about the F/A-18 Forebody-LEX Configuration (1989)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Three-dimensional viscous flow computations are presented for the F/A-18 forebody-LEX geometry. Solutions are obtained from an algorithm for the compressible Navier-Stokes equations which incorporates an upwind-biased, flux-difference-splitting approach along with longitudinally-patched grids. Results are presented for both laminar and fully turbulent flow assumptions and include correlations with wind tunnel as well as flight-test results. A good quantitative agreement for the forebody surface pressure distribution is achieved between the turbulent computations and wind tunnel measurements at Mach number of 0.6. The computed turbulent surface flow patterns on the forebody qualitatively agree well with in-flight surface flow patterns obtained on an F/A-fS aircraft at Mach number of 0.34.
    Keywords: Aerodynamics
    Type: AIAA Paper 89-0338 , 27th Aerospace Sciences Meeting; Jan 09, 1989 - Jan 12, 1989; Reno, NV; United States
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