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6 results on '"residual cutting method"'

1. The generalized residual cutting method and its convergence characteristics.

Author

Abe, T. and Chronopoulos, A. T.

Subjects
*NONSYMMETRIC matrices, *KRYLOV subspace, *SPARSE matrices, *LINEAR systems, *ENGINEERING models
Abstract

Iterative methods and especially Krylov subspace methods (KSM) are a very useful numerical tool in solving for large and sparse linear systems problems arising in science and engineering modeling. More recently, the nested loop KSM have been proposed that improve the convergence of the traditional KSM. In this article, we review the residual cutting (RC) and the generalized residual cutting (GRC) that are nested loop methods for large and sparse linear systems problems. We also show that GRC is a KSM that is equivalent to Orthomin with a variable preconditioning. We use the modified Gram–Schmidt method to derive a stable GRC algorithm. We show that GRC presents a general framework for constructing a class of "hybrid" (nested) KSM based on inner loop method selection. We conduct numerical experiments using nonsymmetric indefinite matrices from a widely used library of sparse matrices that validate the efficiency and the robustness of the proposed methods. [ABSTRACT FROM AUTHOR]

Published
2023
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2. 3D wing flutter analysis by bending-torsion beam model and unstructured CFD

Author

Machida, Kentaro and Miyaji, Koji

Subjects
AGARD 445.6 model, 後退翼, numerical analysis, flutter analysis, 数値解析, bending-torsion beam model, 翼振動, 計算流体力学, AGARD445.6模型, 圧力分布, computational fluid dynamics, 非構造CFD, 残差切除法, sweptback wing, pressure distribution, torsional vibration, wing oscillation, 捩り振動, 曲げ-捩り梁モデル, unstructured CFD, residual cutting method, フラッタ解析
Abstract

A 3D flutter of a sweptback wing is numerically investigated by coupling inviscid flow simulations with a bending-torsion beam structure model. The beam model of a 3D wing is a natural extension of a widely used 2D 2-degree-of-freedom structure model and it considerably simplifies the structure analysis. Finite-volume unstructured CFD is used with the aim of applying various configurations in the future. The grid is dynamically deformed in accordance with the wing motion. A truss-analogy is applied to determine the new positions of interior points when the displacements of boundary points are specified. A well-known experiment using the AGARD standard aeroelastic configuration called 445.6 wing is selected for the validation. The developed methods successfully simulated the experimental flutter boundary., 資料番号: AA0049212015, レポート番号: JAXA-SP-05-017

Published
2006

3. Proceedings of Aerospace Numerical Simulation Symposium 1999

Author

National Aerospace Laboratory

Subjects
計算科学技術, 数値流体力学問題, 回転翼騒音, e(exp N) method, unstructured surface grid generation, finite element method, flow field analysis, multi objective aerodynamic optimization, 多目的空力最適化, 残差切除法, 有限要素法, unstructured adaptive grid refinement, CFD problem, parallel CFD platform, moving overlap grid method, e(exp N)法, 並列計算CFD, computaional fluid dynamics problem, 非構造解適合格子法, 移動重合格子法, 非構造表面格子, global multidisciplinary optimization, blade vortex interaction noise, CFD FEM coupling analysis, 大域的総合最適化, residual cutting method, 流れ場解析, future computational science and engineering, CFD問題, CFDFEM統合数値シミュレーション
Abstract

航空宇宙技術研究所 16-18 Jun. 1999 東京 日本, National Aerospace Laboratory 16-18 Jun. 1999 Tokyo Japan, 以下の主題について論じた。計算科学技術の将来、数値流体力学(CFD)は万能かCFD-EEM(有限要素法)統合数値シミュレーション、大域的総合最適化、移動重合格子法、流れ場解析、非構造解適合格子法、多目的空力最適化、残差切除法、e(exp N)法、非構造表面格子、並列計算CFD、回転翼騒音、高速度民間輸送機、レーザ推進器、スクラムジェットエンジン、最大揚力、HYPR(超音速輸送機用推進システム研究開発)プロジェクト、HOPE-X(宇宙往還技術試験機)空力設計解析。, The following topics were discussed: future computational science and engineering, CFD (Computational Fluid Dynamics), CFD-FEM (Finite Element Method) coupling analysis, global multidisciplinary optimization, moving overlap grid method, flow field analysis, multi objective aerodynamic optimization, residual cutting method, e(exp N) method, unstructured surface grid generation, parallel CFD platform, blade vortex interaction noise, high speed civil transport design, laser propulsion, scram jet engine, HYPR (Super/Hyper-sonic Transport Propulsion System) project, and Hope-X (H-2 Orbiting Plane Experimental) aerodynamic design analysis., 資料番号: AA0001961000, レポート番号: NAL SP-44

Published
1999

4. Residual cutting method using SOR for inner solver

Author

Taniguchi, Koji, Kikuchi, Kazuo, Takahashi, Tadayasu, and Tamura, Atsuhiro

Subjects
逐次過緩和法, 交互方向陰解法, SOR method, 偏微分方程式, ADI法, ポワソン方程式, Poisson equation, 残差切除法, SOR法, partical differential equation, alternating direction implicit method, ADI method, 内部ソルバ, inner solver, residual cutting method, successive over relaxation method
Abstract

航空宇宙技術研究所 16-18 Jun. 1999 東京 日本, National Aerospace Laboratory 16-18 Jun. 1999 Tokyo Japan, 偏微分方程式にたいする高精度数値解法として残差切除法を提案した。以前の報告では、内部ソルバにADI(Alternating Direction Implicit)法を用い良い結果を得た。本稿では、SOR(逐次過緩和)法を内部ソルバとして用い、残差切除法の有効性を研究した。SOR法を内部ソルバに用いた残差切除法は、ロバストで、精度が良く高速であるというよい結果を得た。, The present authors have proposed residual cutting method as a high accurate numerical method for partial differential equations. In these reports, it is used ADI (Alternating Direction Implicit) for inner solver and obtained good results. In this paper, it is used SOR (Successive Over-Relaxation) for inner solver and researched the validity of the Residual Cutting Method. Good results were obtained that the residual cutting method using SOR for inner solver is robust, accurate and fast., 資料番号: AA0001961049, レポート番号: NAL SP-44

Published
1999

5. 曲げ・捩り梁構造モデルと非構造CFDによる3次元翼フラッタ解析

Author

Machida, Kentaro, Miyaji, Koji, 町田 健太郎, 宮路 幸二, Machida, Kentaro, Miyaji, Koji, 町田 健太郎, and 宮路 幸二

Abstract

A 3D flutter of a sweptback wing is numerically investigated by coupling inviscid flow simulations with a bending-torsion beam structure model. The beam model of a 3D wing is a natural extension of a widely used 2D 2-degree-of-freedom structure model and it considerably simplifies the structure analysis. Finite-volume unstructured CFD is used with the aim of applying various configurations in the future. The grid is dynamically deformed in accordance with the wing motion. A truss-analogy is applied to determine the new positions of interior points when the displacements of boundary points are specified. A well-known experiment using the AGARD standard aeroelastic configuration called 445.6 wing is selected for the validation. The developed methods successfully simulated the experimental flutter boundary., JAXA Special Publication, 宇宙航空研究開発機構特別資料

Published
2015

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