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The nas parallel benchmarks
 The International Journal of Supercomputer Applications
, 1991
"... A new set of benchmarks has been developed for the performance evaluation of highly parallel supercomputers. These benchmarks consist of ve \parallel kernel " benchmarks and three \simulated application" benchmarks. Together they mimic the computation and data movement characterist ..."
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Cited by 692 (9 self)
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A new set of benchmarks has been developed for the performance evaluation of highly parallel supercomputers. These benchmarks consist of ve \parallel kernel &quot; benchmarks and three \simulated application&quot; benchmarks. Together they mimic the computation and data movement characteristics of large scale computational uid dynamics applications. The principal distinguishing feature of these benchmarks is their \pencil and paper &quot; speci cation  all details of these benchmarks are speci ed only algorithmically. In this way many of the di culties associated with conventional benchmarking approaches on highly parallel systems are avoided. 1
Aerodynamic design via control theory
 Journal of Scientific Computing
, 1988
"... wing design; optimization. flow; inverse I. INTRODUCTION AND HISTORICAL SURVEY Computers have had a twofold impact on the science of aerodynamics. On the one hand numerical simulation may be used to gain new insights into the physics of complex flows. On the other hand computational methods can be u ..."
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Cited by 321 (63 self)
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wing design; optimization. flow; inverse I. INTRODUCTION AND HISTORICAL SURVEY Computers have had a twofold impact on the science of aerodynamics. On the one hand numerical simulation may be used to gain new insights into the physics of complex flows. On the other hand computational methods can be used by engineers to predict the aerodynamic characteristics of
Numerical Solution Of Problems On Unbounded Domains. A Review
 A review, Appl. Numer. Math
, 1998
"... While numerically solving a problem initially formulated on an unbounded domain, one typically truncates this domain, which necessitates setting the artificial boundary conditions (ABC's) at the newly formed external boundary. The issue of setting the ABC's appears most significant in many ..."
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Cited by 126 (19 self)
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While numerically solving a problem initially formulated on an unbounded domain, one typically truncates this domain, which necessitates setting the artificial boundary conditions (ABC's) at the newly formed external boundary. The issue of setting the ABC's appears most significant in many areas of scientific computing, for example, in problems originating from acoustics, electrodynamics, solid mechanics, and fluid dynamics. In particular, in computational fluid dynamics (where external problems represent a wide class of important formulations) the proper treatment of external boundaries may have a profound impact on the overall quality and performance of numerical algorithms and interpretation of the results. Most of the currently used techniques for setting the ABC's can basically be classified into two groups. The methods from the first group (global ABC's) usually provide high accuracy and robustness of the numerical procedure but often appear to be fairly cumbersome and (computa...
Analysis and Design of Numerical Schemes for Gas Dynamics 1 Artificial Diffusion, Upwind Biasing, Limiters and Their Effect on Accuracy and Multigrid Convergence
 INTERNATIONAL JOURNAL OF COMPUTATIONAL FLUID DYNAMICS
, 1995
"... The theory of nonoscillatory scalar schemes is developed in this paper in terms of the local extremum diminishing (LED) principle that maxima should not increase and minima should not decrease. This principle can be used for multidimensional problems on both structured and unstructured meshes, whi ..."
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Cited by 121 (45 self)
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The theory of nonoscillatory scalar schemes is developed in this paper in terms of the local extremum diminishing (LED) principle that maxima should not increase and minima should not decrease. This principle can be used for multidimensional problems on both structured and unstructured meshes, while it is equivalent to the total variation diminishing (TVD) principle for onedimensional problems. A new formulation of symmetric limited positive (SLIP) schemes is presented, which can be generalized to produce schemes with arbitrary high order of accuracy in regions where the solution contains no extrema, and which can also be implemented on multidimensional unstructured meshes. Systems of equations lead to waves traveling with distinct speeds and possibly in opposite directions. Alternative treatments using characteristic splitting and scalar diffusive fluxes are examined, together with a modification of the scalar diffusion through the addition of pressure differences to the momentum equations to produce full upwinding in supersonic flow. This convective upwind and split pressure (CUSP) scheme exhibits very rapid convergence in multigrid calculations of transonic flow, and provides excellent shock resolution at very high Mach numbers.
Solution of the Euler equations for two dimensional transonic flow by a multigrid method
 Appl Math Comput
, 1983
"... A crucial input to the design of a long range aircraft is the prediction of the aerodynamic flow in cruising flight. In contrast to the flow past a blunt object, such as a golf ball, or ski racer, the flow past an aircraft generally does not separate. Consequently, the important viscous effects are ..."
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Cited by 103 (23 self)
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A crucial input to the design of a long range aircraft is the prediction of the aerodynamic flow in cruising flight. In contrast to the flow past a blunt object, such as a golf ball, or ski racer, the flow past an aircraft generally does not separate. Consequently, the important viscous effects are mainly confined to boundary layers over the surface of the aircraft, and useful predictions can be made by solving the equations of inviscid flow. The cruising
Calculation of Inviscid Transonic Flow over a Complete Aircraft
 AIAA Paper 860103, AIAA 24th Aerospace Sciences Meeting
, 1986
"... U.S.A. We present preliminary results for the calculation of inviscid transonic
ow over a complete aircraft. These results have been obtained by a novel approach that combines a new procedure for mesh generation with a new nite element method for solving the Euler equations. ..."
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Cited by 85 (23 self)
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U.S.A. We present preliminary results for the calculation of inviscid transonic
ow over a complete aircraft. These results have been obtained by a novel approach that combines a new procedure for mesh generation with a new nite element method for solving the Euler equations.
Multiscale scientific computation: Review 2001
 Multiscale and Multiresolution Methods
, 2001
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A Perspective on Computational Algorithms for Aerodynamic Analysis and Design
 Progress in Aerospace Sciences
, 2001
"... This paper exam nes the use of computational fluid dynamics as a tool for aircraft design. It addresses the requirements for effective industrial use, and tradeoffs between modeling accuracy and computational costs. Essential elements of algorithm design are discussed in detail, together with a uni ..."
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Cited by 57 (19 self)
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This paper exam nes the use of computational fluid dynamics as a tool for aircraft design. It addresses the requirements for effective industrial use, and tradeoffs between modeling accuracy and computational costs. Essential elements of algorithm design are discussed in detail, together with a unified approach to the design of shock capturing schemes. Finally, the paper discusses the use of techniques drawn from control theory to determine optimal aerodynamic shapes. In the future multidisciplinary analysis and optimization should be combined to take account of the tradeoffs in the overall performance of the complete system
Symmetrypreserving discretization of turbulent flow
 J. Comp. Phys
, 2003
"... We propose to perform turbulent flow simulations in such manner that the difference operators do have the same symmetry properties as the underlying differential operators, i.e., the convective operator is represented by a skewsymmetric coefficient matrix and the diffusive operator is approximated ..."
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Cited by 49 (5 self)
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We propose to perform turbulent flow simulations in such manner that the difference operators do have the same symmetry properties as the underlying differential operators, i.e., the convective operator is represented by a skewsymmetric coefficient matrix and the diffusive operator is approximated by a symmetric, positivedefinite matrix. Mimicking crucial properties of differential operators forms in itself a motivation for discretizing them in a certain manner. We give it a concrete form by noting that a symmetrypreserving discretization of the Navier–Stokes equations is stable on any grid, and conserves the total mass, momentum and kinetic energy (for the latter the physical dissipation is to be turned off, of coarse). Being stable on any grid, the choice of the grid may be based on the required accuracy solely, and the main question becomes: how accurate is a symmetrypreserving discretization? Its accuracy is tested for a turbulent flow in a channel by comparing the results to those of physical experiments and previous numerical studies. The comparison is carried out for a Reynolds number of 5600, which is based on the channel width and the mean bulk velocity (based on the channel halfwidth and wall shear velocity the Reynolds number becomes 180). The comparison shows that with a fourthorder, symmetrypreserving method a 64 64 32 grid suffices to perform an accurate numerical simulation.