서지주요정보
비정렬 혼합격자계에서 비정상 유동 해석을 위한 고차정확도 해석 기법 연구 = NumeRICAL INVESTIGATION OF A HIGH-ORDER ACCURATE METHOD FOR UNSTEADY FLOW SIMULATION ON MIXED UNSTRUCTURED MEShes
서명 / 저자 비정렬 혼합격자계에서 비정상 유동 해석을 위한 고차정확도 해석 기법 연구 = NumeRICAL INVESTIGATION OF A HIGH-ORDER ACCURATE METHOD FOR UNSTEADY FLOW SIMULATION ON MIXED UNSTRUCTURED MEShes / 정민규.
발행사항 [대전 : 한국과학기술원, 2014].
Online Access 원문보기 원문인쇄

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8026100

소장위치/청구기호

학술문화관(문화관)B1층 보존서고

DAE 14005

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In the present study, a high-order accurate flow solver based on a mixed mesh paradigm has been developed for the numerical simulation of unsteady flows. The proposed mesh topology involves unstructured tetrahedral/prismatic mesh in the near-body region and adaptive Cartesian mesh in the off-body region. The body-conforming near-body unstructured mesh offers a great flexibility in treating complex geometries, and also ensures proper mesh resolution for capturing the boundary layer. For the Cartesian mesh in the off-body region, a high-order accurate WENO (Weighted Essentially Non-Oscillatory) scheme was adopted to better resolve the detailed flow features. A multi-level mesh adaptation scheme with a tree-based data structure was also employed directly on the Cartesian cells to further enhance the accuracy of the solution. To transfer the flow information between the two mesh topologies, an overset mesh technique was applied. To assess the accuracy of the present flow solver, various two- and three-dimensional validation cases were examined. From these numerical investigations, it was concluded that the present mixed mesh flow solver with high-order scheme and adaptive mesh refinement is more accurate and efficient for steady and unsteady flow simulations, compared to traditional unstructured mesh flow solver.

본 연구에서는 비정상 유동에 대한 수치해석을 위해 비정렬 혼합 격자기반의 고차정확도의 유동 해석자를 개발하였다. 개발된 해석자는 물체와 인접한 영역에서는 비정렬의 사면체와 프리즘 격자를 반면에 물체와 떨어진 영역에서는 적응 직교격자를 이용하였다. 물체 주변의 비정렬 격자의 경우 복잡한 형상에 대해서도 격자 생성이 용이하다는 장점을 가지고 있으며, 동시에 물체 표면에서 나타나는 경계층 유동에 대해서도 정확한 해석이 가능하다는 장점을 가지고 있다. 반면 직교격자 영역에서는 WENO 스킴에 기반한 고차정확도 기법 적용함으로써 물체와 떨어진 영역에서도 보다 정확한 해석이 가능케 구현되었다. 또한 국부적으로 나타나는 주요한 유동 특성, 예를 들면 충격파나 와류유동과 같은 유동 현상들을 효율적으로 모사하기 위해 격자 적응 기법을 활용하였다. 격자 적응 기법은 트리 자료 구조를 활용함으로써 자동화 및 강건성을 확보하였다. 두 가지 형태의 격자기법을 활용함으로써 격자계간 유동변수의 내삽이 요구되는데 이를 위해 중첩격자기법이 활용되었다. 개발된 해석자는 2차원과 3차원의 다양한 문제에 적용하였다. 3차원의 실제 헬리콥터 형상에 개발된 해석자를 적용하였으며, 이를 통해 충격파와 블레이드-와류의 간섭현상 등을 모사하였다. 수치해석을 통해 본 연구에서 제안한 혼합격자 해석자가 기존에 사용하던 비정렬 격자계의 해석자보다 정상 및 비정상 유동 해석에 있어 보다 정확하고 효율적으로 계산이 수행됨을 확인할 수 있었다.

서지기타정보

서지기타정보
청구기호 {DAE 14005
형태사항 vii, 120 p. : 삽화 ; 30 cm
언어 한국어
일반주기 저자명의 영문표기 : Min-Kyu Jung
지도교수의 한글표기 : 권오준
지도교수의 영문표기 : Oh-Joon Kwon
학위논문 학위논문(박사) - 한국과학기술원 : 항공우주공학전공,
서지주기 참고문헌 : p. 112-117
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이 주제의 인기대출도서

Dual-mesh paradigm used in the Helios code with unstructured near-body grids to capture geometric features and boundary layer near the body surface, and block-structured Cartesian grids to capture far-field flow features.

Software infrastructure utilized in Helios.

Block-structured AMR grid containing a hierarchy of nested refinement levels.

Grid system and iso-surface of vorticity for 3D NACA0015 Wing simulation

Vortical strengh is measured at three downstream locations by extracting a spanwise line, which passes through the core, ofz-velocity data.

Experimental and computed rotor thrust and torque coefficient, the figures of merit, and the associated error with and without solution-based adaptation in the off-body mesh.

The TRAM near-body unstructured gridwith the unadapted off-body Cartesian gridsystem

TRAM solutions generated with and without solution-based adaptation when the non- dimensional Q method is used to guide the AMR process. A y-cut plane dipicts the off-body grid, and the isosurfaces shown represent equivalent values ofQ, which are colored by vorticity magnitude.

Construction of a sub-cell for tetrahedral, pyramidal, and prismatic element

Construction of a median-dual surface and an equivalent surface.

Two kinds of interpolations for WENO calculations

Neighbor cells for multidimensional interpolations.

Strengths and Weaknesses of Various Adaptation Criteria

Threshold for adaptation : Refinement and Coarsening

Description of physical and virtual control volume on the process of partitioning

Domain decomposition using minimum depth tree.

Choice of starting point for robust searching.

Comparison of vertex searching direction at an airfoil trailing edge.

Concept of linear shape-function searching alogrithm

Linear shape function N2N searching.

Inner product N2N searching.

Iso-parametric coordinate of cell element.

Distance-to-Wall algorithm[57].

Cell element distinction procedure based on the index of vertices.

Spatial order of accuracy on the off-body region after hole cutting procedure.

Determination of interpolation receiver and donor.

Stencils for interpolation of flow variables.

Treatment of interpolation stencil inside solid wall boundary.

Density contour of a stationary vortex after 10 seconds using WENO5

Distribution of density across vortex core after 10 seconds using WENO5 and 1st order scheme.

Computational mesh for comparison with and without high order interpolation

Number of computational cells ofa convecting vortex at t = 10,t= 20,t=30.

Comparison of density Contours for a stationary vortex with and without high order inter- polation.

Computational meshes and density contours ofa convecting vortex using the WENO5 scheme

Comparison of density Contours for a convecting vortex using WENO5 and 2nd order scheme.

Schematic of the double Mach reflection.

Computational meshes and density contours of the double Mach reflection using WENO:

Off-body and near-body meshes for an NACA0012 airfoil at Moo = 0.7, AOA=4.

Computational meshes and Pressure contours for an NACA0012 airfoil at Mco = 0.7 AOA=48.

Pressure coefficient distribution for an NACA0012 airfoil at Mo = 0.7, AOA=45

Instantaneous pressure contours for a pitching NACA0012 airfoil.

Aerodynamic force and moment for a pitching NACA0012 airfoil.

Numerical meshes and vorticity contours at three instantaneous angles of attack f pitchino NACA0012 airfoil

Numerical meshes and vorticity contours with mesh adaptation at three instantaneo angles of attack for a pitching NACA0012 airfoil.

Aerodynamic force and moment histories for a pitching NACA0012 airfoil during one cycle of harmonic motion.

Computational meshes for NACA 0015 wing.

A comparison of wake structures represented by iso->2 surface according to the order of accuracy for NACA 0015 wing.

Normalized z-directional velocity distributions in wake region for NACA 0015 wing

Adaptive meshes and wake structures represented by iso->2 surface on the AMR proces for NACA 0015 wing.

Numerical meshes and ㅅ2 Contours at two and six chords downstream.

Normalized z-directional velocity distributions in wake region for NACA 0015 wing

Volume mesh and surface mesh for Caradonna-Tung rotor.

Wake structure comparison by order of accuracy for Caradonna-Tung rotor in hover

Vorticity contour comparison by order of accuracy for Caradonna-Tung rotor in hover.

Predicted and experimental vortex trajectories of Caradonma-Tung rotor in hover

Compasion of spanwise sectional thrust coefficient distributions of Caradonma-Tung rotor in hover.

Comparison of pressure coefficient distributions on the blade of Caradonma-Tung rotor ir hover.

Numerical meshes and contours with initial mesh of Caradonna-Tung rotor in hover.

Numerical meshes and contours with adaptive mesh of Caradonna-Tung rotor in hover.

Predicted and experimental vortex trajectories with initial and adaptive meshes of Caradonna-Tung rotor in hover.

Mesh information for HART II rotor.

Numerical meshes for HART II rotor.

Wake structure and vorticity contours for HART II rotor in forward flight.

Sectional force/moment at 87% span for HART II rotor in forward flight.

Tip vortex position for HART II rotor in forward fight.

Tip vortex position on y/R = 土0.7 plane for HART II rotor in forward flight.

Adaptive meshes for HART II rotor in forward flight.

Wake structure and vorticity contours with adaptive meshes for HART II rotor in forward flight.

Comparison of Sectional force/moment at 87% span by using mesh adaptation for HART II rotor in forward flight.

Tip vortex position with adaptive meshes for HART II rotor in forward flight

Tip vortex position ony/R= 士0.7 plane with adaptive meshes for HART II rotor in forward flight.

Schematic of the parallel BVI test.

Mesh information for parallel BVI test.

Numerical meshes for parallel BVI test.

Wake structures with miss distance for parallel BVI test.

Pressure contours with miss distance for parallel BVI test.

Difference of upper and lower pressure coefficient with miss distance for parallel BVI test.

Wake structures with direct impact for parallel BVT test

Pressure contours with direct impact for parallel BVI test.

Difference of upper and lower pressure coefficient with direct impact for parallel BVI test.