• Structural Engineering and Mechanics
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• 제73권1호
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• pp.65-73
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• 2020

The present work describes a new time marching procedure for structural dynamics analyses. In this novel technique, time integration parameters are automatically evaluated according to the properties of the model. Such parameters are locally defined, allowing the user to input a numerical dissipation property for each element, which defines the amount of numerical dissipation to be introduced. Since the integration parameters are locally defined as a function of the structural element itself, the time marching technique adapts according to the model, providing enhanced accuracy. The new methodology is based on displacement-velocity relations and no computation of accelerations is required. Furthermore, the method is second order accurate, it has guaranteed stability, it is truly self-starting and it allows highly controllable algorithm dissipation in the higher modes. Numerical results are presented and compared to those provided by the Newmark and the Bathe methods, illustrating the good performance of the new time marching procedure.

• 대한기계학회논문집
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• 제18권7호
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• pp.1840-1850
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• 1994

Enhancement of numerical algorithms for low speed compressible flow will be considered. Contemporary time-marching algorithm has been widely accepted and applied as the method of choice for transonic, supersonic and hypersonic flows. In the low Mach number regime, time-marching algorithms do not fare as well. When the velocity is small, eigenvalues of the system of compressible equations differ widely so that the system becomes very stiff and the convergence becomes very slow. This characteristic can lead to difficulties in computations of many practical engineering problems. In the present approach, the time-derivative preconditioning method will be used to control the eigenvalue stiffness and to extend computational capabilities over a wide range of flow conditions (from very low Mach number to supersonic flow). Computational capabilities of the above algorithm will be demonstrated through computation of a variety of practical engineering problems.

• International Journal of Aeronautical and Space Sciences
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• 제1권1호
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• pp.1-12
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• 2000

The wake geometries of a two-bladed rotor in axial flights using a time-marching free-wake method without a non-physical model of the far wake are calculated. The computed free-wake geometries of AH-1G model rotor in climb flight are compared with the experimental visualization results. The time-marching free-wake method can predict the behavior of the tip vortex and the wake roil-up phenomena with remarkable agreements. Tip vortices shed from the two-bladed rotor can interact with each other significantly. The interaction consists of a turn of the tip vortex from one blade rolling around the tip vortex from the other. Wake expansion of wake geometries in radial direction after the contraction is a result of adjacent tip vortices begging to pair together and spiral about each other. Detailed numerical results show regular pairing phenomenon in the climb flights, the hover at high angle of attack and slow descent flight too. On the contrary, unstable motions of wake are observed numerically in the hover at low angle of attack and fast descent flight. It is because of the inherent wake instability and blade-vortex-interaction rather then the effect of recirculation due to the experimental equipment.

• International Journal of Aeronautical and Space Sciences
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• 제5권2호
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• pp.62-70
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• 2004

CFD method has been coupled with a time-marching free-wake model by usingfield velocity approach suggested by J. D. Baeder (Ref. 1). The coupled method hasbeen applied to rectangular and BERP-like blades and the calculated perfonnance dataare compared with the experimental results.For hovering analysis, the present method could yield sufficiently good resultswith reasonable computation time and is particularly suitable for the flow fieldanalysis with the complex shaped blade.

• 한국컴퓨터그래픽스학회논문지
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• 제24권1호
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• pp.1-8
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• 2018

본 논문에서는 삼각형 집합(triangle soup)형식의 등가면(isosurface)을 추출하는 기존의 마칭큐브 기법을 개선하여, 연결된 메시(connected mesh)형식으로 추출하는 실시간 기법을 제안한다. 이를 통해 기존에는 불가능했던 다양한 렌더링 기법을 사용하여 동적으로 변하는 등가면을 렌더링할 수 있고, 등가면의 위상(topology)과 기하(geometry) 정보 등을 추출할 수 있다. 또한 지오메트리 셰이더 (geometry shader) 에서 사용하는 인접 삼각형 형태의 구조 (GL_TRIANGLES_ADJACENCY)를 생성하여 보다 다양한 셰이딩 기법을 지원한다. 본 기법은 기존 마칭큐브에 삼각형들을 연결하는 후처리 과정을 추가한 기법에 비해 300% 정도의 향상된 등가면 추출 속도를 보인다.

• 한국추진공학회:학술대회논문집
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• 한국추진공학회 2004년도 제22회 춘계학술대회논문집
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• pp.15-25
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• 2004

This paper outlines a new convergence acceleration de-signed to solve scramjet flowfields with zones of re-circulation. Named the “marching-window”, the algorithm consists of performing pseudo-time iterations on a minimal width subdomain composed of a sequence of cross-stream planes of nodes. The upstream boundary of the subdomain is positioned such that all nodes upstream exhibit a residual smaller than the user-specified convergence threshold. The advancement of the downstream boundary follows the advancement of the upstream boundary, except in zones of significant streamwise ellipticity where a streamwise ellipticity sensor ensures its continuous progress. Compared to the standard pseudo-time marching approach, the march-ing-window is here seen to decrease the work required for convergence by up to 24 times for supersonic flows with little streamwise ellipticity and by up to 8 times for supersonic flows with large streamwise separated regions. The memory requirements are observed to be reduced sixfold by not allocating memory to the nodes not included in the computational subdomain. The marching-window satisfies the same convergence criterion as the standard pseudo-time stepping methods, hence resulting in the same converged solution within the tolerance of the user-specified convergence threshold. The extension of the marching-window to the weakly-ionized Navier-Stokes equations is also discussed.

• 한국항공우주학회지
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• 제37권4호
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• pp.329-335
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• 2009

비정상 패널법과 시간 전진 자유 후류법을 연계하여 제자리 및 수직 비행 하는 헬리콥터 로터의 공력 및 익단와류를 검증하였다. 검증된 수치 방법을 이용하여 저속 하강 비행하는 로터에서 발생하는 BVI(Blade Vortex Interaction)의 비정상 공력을 해석 하고 이때 나타나는 익단 와류에 의한 공력의 변화를 고찰하였다.

• 한국전산유체공학회지
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• 제20권1호
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• pp.32-38
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• 2015

A 3-dimensional compressible turbulent boundary layer solver has been developed. A time marching method is used to integrate the turbulent boundary layer equations. While the direct integration of the boundary layer equations is performed for unseparated flow regions, the inverse integration is performed for separated flow regions. The program is verified for flows that have analytical solutions or other numerical results. The solver will be merged with an Euler solver for viscous-inviscid interaction.

• 한국군사과학기술학회지
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• 제9권2호
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• pp.152-160
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• 2006

Time marching methods are well-suited for high speed compressible flow computations. However, it is well known that the time marching methods suffer a slow down in convergence due to disparity in Eigenvalues. A local preconditioning method is one of numerical methods to enhance convergence characteristics of low mach number flows by modifying Eigenvalues of the governing equations. In this paper, the local preconditioning method of Weiss is applied to a 2 dimensional Navier-Stokes code and the efficiency of the preconditioning method is shown through a number of computational examples.

• 한국컴퓨터그래픽스학회논문지
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• 제26권4호
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• pp.17-26
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• 2020

본 논문에서는 GPU(Graphic Processing Unit) 연산을 활용하여 BCC(Body Centered Cubic) 볼륨 데이터로부터 실시간으로 메시 형태의 등가면을 추출하는 개선된 마칭 사면체(Marching tetrahedra) 기법을 제안한다. 본 기법은 고전적인 방법과 비교하여 메모리 사용량은 다소 높지만 더 좋은 성능을 보인다. 본 기법은 다섯 단계로 구성되어 있다. 첫 번째 단계는 단 한번만 수행되는 단계로, 빈 공간을 생략하여 성능을 향상 시키기 위해 최소/최댓값 블록(Min/max block)을 생성한다. 두 번째 단계에서는 등갓값(Isovalue)을 포함하고 있는 유효한 블록을 추려낸다. 이후 두 단계에서는 등가면(Isosurface)을 포함하는 셀(Cell)과 엣지(Edge)를 추출하고, 마지막 단계에서 삼각형 메시(Triangle mesh)를 생성한다. 본 기법은 512³ 이상의 고해상도 볼륨 데이터(Volume dataset)에 대한 등가면 추출 시, 삼각형 집합 형태의 등가면을 추출하는 고전적인 마칭 사면체 기법에 비해 최대 5배 정도의 속도 향상을 보인다.