Proceedings ArticleDOI
Recent enhancements to OVERFLOW
TLDR
The purpose of this paper is to highlight some recent enhancements that have been made to the Navier-Stokes code OVERFLOW, in three major areas: a multigrid method, for convergence acceleration; a lowMach preconditioning algorithm, for converge acceleration and solution quality improvement for low Mach number flows; and a matrix dissipation algorithm for solution quality improved.Abstract:
The purpose of this paper is to highlight some recent enhancements that have been made to the Navier-Stokes code OVERFLOW. The enhancements we are concerned with are in three major areas: a multigrid method, for convergence acceleration; a lowMach preconditioning algorithm, for convergence acceleration and solution quality improvement for low Mach number flows; and a matrix dissipation algorithm for solution quality improvement. We will describe these methods and show examples of their efficacy.read more
Citations
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Patent
Generating a simulated fluid flow over an aircraft surface using anisotropic diffusion
David L. Rodriguez,Peter Sturdza +1 more
TL;DR: In this article, a diffusion-path vector is defined between a point in the selected polygon and a neighboring point in a neighboring polygon, and an updated fluid property is determined for the selected polygons using a variable diffusion rate, the variable diffusion rates based on the minimum diffusion rate and angular difference between the diffusion path vector and the pressure gradient vector.
CFD-Based HPCMP Systems Assessment Using AERO, AVUS, and OVERFLOW-2
Sam B. Cable,Thomas C. Oppe,W.A. Ward,R.E. Gordnier,V.S. Burnley,M.J. Grismer,Roy L. Campbell,P.G. Burning +7 more
TL;DR: In this paper, the authors compare the performance of the major HPCMP architectures in executing each of the following CFD application test cases found within the TI-05 benchmarking suite: AERO, AVUS, and OVERFLOW 2 standard/large.
Journal ArticleDOI
Experimental and Computational Investigation of Blunt Trailing-Edge Airfoils with Splitter Plates
TL;DR: Experimental and computational examinations of the effect of splitter plate length on the aerodynamic performance and vortex shedding behavior of a blunt trailing-edge airfoil are presented along w... as discussed by the authors.
Book ChapterDOI
Optimization of Panels with Riveted Z-shaped Stiffeners via PANDA2
TL;DR: The PANDA2 computer program has been modified to permit minimum weight design of imperfect panels with riveted Z-shaped stiffeners for service in a load regime in which the panel is in its locally postbuckled state as mentioned in this paper.
Improvement of crossflow aerodynamic predictions for forward flight at all advance ratios
Joachim Hodara,Marilyn J. Smith +1 more
TL;DR: In this paper, the impact of crossflow on forward flight performance of an infinite yawed wing was analyzed for use in airfoil tables (C81 tables) for rotorcraft comprehensive codes.
References
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Book
An Introduction to Multigrid Methods
TL;DR: These notes were written for an introductory course on the application of multigrid methods to elliptic and hyperbolic partial differential equations for engineers, physicists and applied mathematicians, restricting ourselves to finite volume and finite difference discretization.
Journal ArticleDOI
A diagonal form of an implicit approximate-factorization algorithm
Thomas H. Pulliam,D.S Chaussee +1 more
TL;DR: The modification transforms the coupled system of equations into an uncoupled diagonal form that requires less computational work and has an important effect on the application of implicit finite-difference schemes to vector processors.
Journal ArticleDOI
Preconditioned methods for solving the incompressible low speed compressible equations
TL;DR: It is sown that the resultant incompressible equations form a symmetric hyperbolic system and so are well posed, and several generalizations to the compressible equations are presented which extend previous results.
Proceedings ArticleDOI
A 3-D Chimera Grid Embedding Technique
TL;DR: A three-dimensional (3-D) chimera grid-embedding technique that simplifies the construction of computational grids about complex geometries by solution of the Euler equations for the transonic flow about a wing/body, wing/ body/tail, and a configuration of three ellipsoidal bodies is described.