First TAU Theory and Praxis Training From CAD to Grid
|
|
|
- Arleen Stewart
- 5 years ago
- Views:
Transcription
1 First TAU Theory and Praxis Training From CAD to Grid S. Melber-Wilkending
2 First TAU Theory and Praxis Training From CAD to Grid or How to use the Centaur-Grid-Generator S. Melber-Wilkending
3 Outline Introduction Demonstration of Centaur: RAE 2822 Airfoil ONERA M6 Wing Generic Wing/Body/Engine Config. Individual CENTAUR User Training
4 Introduction Grid-generators used in the institute: Centaur, GridGen, SOLAR, MegaCads focus on Centaur (hybrid unstructured) Presentation can/should be used as Handbook for first steps with CENTAUR Handbook with complete description of CENTAUR: Login: dlrbs, PWD: alvwal CENTAUR is a complex tool, the best way is Learning by doing Individual user training at the end of this talk Used Software: CENTAUR grid generator Viscalc (boundary layer calculation) Tecplot (visualization) First: Examples of CENTAUR grids build at DLR
5 Examples of CENTAUR grids
6 Examples of CENTAUR grids
7 Examples of CENTAUR grids
8 Examples of CENTAUR grids
9 Examples of CENTAUR grids
10 Examples of CENTAUR grids
11 Examples of CENTAUR grids
12 Examples of CENTAUR grids
13 Examples of CENTAUR grids
14 Examples of CENTAUR grids
15 Examples of CENTAUR grids
16 Examples of CENTAUR grids
17 Examples of CENTAUR grids
18 Examples of CENTAUR grids
19 Examples of CENTAUR grids
20 RAE 2822 transonic airfoil (2D-case)
21 RAE 2822 Airfoil (1) Case: RAE 2822 transonic airfoil (2D-case) Grid: Euler grid Commands: Setupgrid rae.dat Switch to 2d mode? -> Yes Define boundary conditions: Create Group Group Name -> Farfield Type -> Triangles Boundary Condition -> Farfield Select curves 1,2 -> Move All
22 Setupgrid Hotkeys Setupgrid: Selection / Translation / Rotation / Zoom Hotkey r : rotation mode Hotkey t : translation mode Hotkey z : zoom mode Hotkey s : selection mode Hotkey q : query mode Setupgrid input formats: *.dat: native Centaur-format (written e.g. by MegaCads, CadFix) *.igs: common CAD-format (written e.g. by Catia, CadFix )
23 RAE 2822 Airfoil (1) Case: RAE 2822 transonic airfoil (2D-case) Grid: Euler grid Commands: Setupgrid rae.dat Switch to 2d mode? -> Yes Define boundary condition: Create Group Group Name -> Farfield Type -> Triangles Boundary Condition -> Farfield Select curves 1,2 -> Move All Create Group Group Name -> Airfoil Type -> Triangles Boundary Condition -> Inviscid Wall Select curves 3,4 -> Move All
24 RAE 2822 Airfoil (2) Case: RAE 2822 transonic airfoil (2D-case) Grid: Euler grid Commands: Build initial files for grid generation: File -> Write output files -> rae Starting grid generation: makegrid rae Visualize final grid: Hybconvert rae.hyb -> Tecplot Format Binary Tecplot rae.hyb.plt Grid is a bit coarse...!
25 Stages & Inputfiles of Grid Generation Centaur grid generation is running in three stages: 1. Surface grid boundaries of the grid 2. Prism/Hexa grid boundary layer (only for NavierStokes grids) 3. Tetrahedral grid rest of the domain Important Input-files for grid generation: Surface input-file [case].sin: for the control of the surface-grids Prismatic input-file [case].pin: for the control of the prism/hexa-grids Tetrahedra input-file [case].tin: for the control of the tetrahedral-grids User defined sources: Source file [case].lin
26 RAE 2822 Airfoil (3) Case: RAE 2822 transonic airfoil (2D-case) Grid: Euler grid Commands: Global refinement of surface (located in rae.sin-file): Length Scale in absence of any features: 0.01 Global refinement of farfield (located in rae.tin-file): Stretching ratio: 1.8
27 RAE 2822 Airfoil (4) Case: RAE 2822 transonic airfoil (2D-case) Grid: Navier-Stokes grid Commands: Change boundary condition in setupgrid Set Group -> Airfoil Modifiy Group Type -> Quads Boundary Condition -> Viscous Wall Write output files Overwrite existing input files -> Yes Refine Surface and Farfield: sin-file: Length Scale in absence of any features: 0.01 Tin-file: Stretching ratio: 1.8
28 Boundary Layer Resolution (1) Prism/Hexa-grids are controlled by three parameters: Number of layers n Initial marching step y1 Stretching ratio q The final prism-layer thickness sn can be calculated from a geometrical series: sn = y1 * (qn-1) / (n-1) Initial marching step can be determined from y+ = 1 Number of layers is determined by the user Stretching ratio can be Set by the user Calculated from a given prism layer thickness sn
29 Boundary Layer Resolution (2) Calculation of the stretching ratio q: Calculation of the boundary layer thickness using the analogy of an flat plate Assumption: prism layer has (minimum) the same thickness as the boundary layer Program Viscalc: Compile: cc o viscalc viscalc.c -lm Input: Re, Ma, T, y+ Output: n (given q) q (given n)
![RAE 2822 Airfoil (5) Case: RAE 2822 transonic airfoil (2D-case) Grid: Navier-Stokes grid Commands: Change boundary-layer grid ([case].](/docs-images/89/100204108/images/30-2.jpg "pin-file) using data calculated with Viscalc final grid Attention: the minimum nominal marching step has to be about 1/10 of the initial marching step!")
30 RAE 2822 Airfoil (5) Case: RAE 2822 transonic airfoil (2D-case) Grid: Navier-Stokes grid Commands: Change boundary-layer grid ([case].pin-file) using data calculated with Viscalc final grid Attention: the minimum nominal marching step has to be about 1/10 of the initial marching step! After finalizing a grid: makegrid [case] clean to save disc space
31 ONERA M6 Wing (3D-case)
32 ONERA M6 Wing (1) Case: Simple trapezoid wing (3D-case) Grid: Navier-Stokes grid Commands: Setupgrid M6.dat Create Group -> Farfield (Tetrahedra, Farfield) Select panels & Move All Create Group -> Symmetry (Hybrid, Symmetry) Select panels & Move All Create Group -> Wing (Prism, Viscous Wall) Select panels & Move All Write Output files -> m6
33 ONERA M6 Wing (2) Case: Simple trapezoid wing (3D-case) Grid: Navier-Stokes grid Commands: Calculate prism layer with Viscalc Put data in m6.pin makegrid m6 Visualize final grid: hybconvert m6.hyp Visualize surface grid: hybconvert m6.fvs Grid is to coarse on the nose: Increase Factor for curvature clustering: 40 in m6.sin Re-build surface grid: makegrid m6 surface To much cells in span-wise direction: Build panel-source Anisotropy in Setupgrid Direction of anisotropy: u-direction (full lines) Change of u/v-direction: setupgrid CAD -> Panels -> Swap u/v for selected panels
34 Sources in CENTAUR Sources: To add points to the mesh where extra resolution is needed To control locally features of the grid The sources are created with setupgrid Different types of sources available: Geometric: Point, Line, Quadrilateral, Hexahedron, Sphere, Cylinder, Cone, Frustum CAD: Curve, Panel, Group
35 ONERA M6 Wing (3) Case: Simple trapezoid wing (3D-case) Grid: Navier-Stokes grid Commands: Define a Cylinder-source for surface and tetrahedra above the wing to improve shock resolution: Surface / Tetrahedra 0.01, Radius 0.2 To define a source use of /Tools/Point List/Add highlighted to point list
36 Chopping Generation of different number of prism layers over the geometry e.g. Figure: only one layer of prisms can fit in the cavity, but the full 5 layers can be generated elsewhere
37 Chopping Generation of different number of prism layers over the geometry e.g. Figure: only one layer of prisms can fit in the cavity, but the full 5 layers can be generated elsewhere Advantages: In regions of small cavities, growing full prism layers results in very fine cells reduction the time step in flow solvers The tetrahedra are forced to match the length scales of the final prism layer. A small final layer thickness resulting in very large meshes (small elements) or a crash of the tetrahedra-stage Technique: Iterative reduction of the marching step to minimum allowable marching step If the algorithm requires marching steps smaller than this value, instead of reducing the marching step further, the number of layers are reduced effectively reduce the overall prismatic layer thickness
38 ONERA M6 Wing (4) Case: Simple trapezoid wing (3D-case) Grid: Navier-Stokes grid Commands: Demonstration of chopping: Create a point source with number of prism layers eq. zero Visalize final prims layer (hybconvert m6.fvp) Remember: Outputfiles from Centaur [case].fvs: surface grid [case].fvp: BL-Grid [case].hyb: final grid
39 Generative Wing/Body/Engine Configuration (3D-case)
40 Generative Wing/Body/Engine Configuration (1) Case: Half-Model Wing/Body/Engine Configuration (3D-case) Grid: Navier-Stokes grid Commands: CAD-Cleaning: Setupgrid gen.unclean.igs View By -> Curve: red curves, means problems in CAD data CAD-cleaning: CAD -> Curve -> Merge selected curves Split selected curves Attention: possible change of CAD geometry! Small, unneeded curves can be killed (CAD-fragments) Automatic Diagnostic / Cleaning: CAD -> Run CAD Diagnostics CAD -> Run CAD Cleaning
41 Generative Wing/Body/Engine Configuration (2) Case: Half-Model Wing/Body/Engine Configuration (3D-case) Grid: Navier-Stokes grid Commands: Set Farfield, Symmetrie, Wing, Body,Tail, Engine, Pylon Panels Set prism layer data Generate grid...
42 Generative Wing/Body/Engine Configuration (3) Case: Half-Model Wing/Body/Engine Configuration (3D-case) Grid: Navier-Stokes grid Commands: Convert CENTAUR to TAU-grid: centaur2tau [case.hyb]
43 and now its time to generate your own grids
TAU mesh deformation. Thomas Gerhold
TAU mesh deformation Thomas Gerhold The parallel mesh deformation of the DLR TAU-Code Introduction Mesh deformation method & Parallelization Results & Applications Conclusion & Outlook Introduction CFD
HPC Computer Aided CINECA
HPC Computer Aided Engineering @ CINECA Raffaele Ponzini Ph.D. CINECA SuperComputing Applications and Innovation Department SCAI 16-18 June 2014 Segrate (MI), Italy Outline Open-source CAD and Meshing
Viscous Hybrid Mesh Generation
Tutorial 4. Viscous Hybrid Mesh Generation Introduction In cases where you want to resolve the boundary layer, it is often more efficient to use prismatic cells in the boundary layer rather than tetrahedral
Challenges in Boundary- Layer Stability Analysis Based On Unstructured Grid Solutions
Challenges in Boundary- Layer Stability Analysis Based On Unstructured Grid Solutions Wei Liao National Institute of Aerospace, Hampton, Virginia Collaborators: Mujeeb R. Malik, Elizabeth M. Lee- Rausch,
Recent developments for the multigrid scheme of the DLR TAU-Code
www.dlr.de Chart 1 > 21st NIA CFD Seminar > Axel Schwöppe Recent development s for the multigrid scheme of the DLR TAU-Code > Apr 11, 2013 Recent developments for the multigrid scheme of the DLR TAU-Code
AN INVERSE DESIGN METHOD FOR ENGINE NACELLES AND WINGS
24th INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES AN INVERSE DESIGN METHOD FOR ENGINE NACELLES AND WINGS Roland Wilhelm German Aerospace Center DLR, Lilienthalplatz 7, D-388 Braunschweig, Germany
FAR-Wake Workshop, Marseille, May 2008
Wake Vortices generated by an Aircraft Fuselage : Comparison of Wind Tunnel Measurements on the TAK Model with RANS and RANS-LES Simulations T. Louagie, L. Georges & P. Geuzaine Cenaero CFD-Multiphysics
A Scalable GPU-Based Compressible Fluid Flow Solver for Unstructured Grids
A Scalable GPU-Based Compressible Fluid Flow Solver for Unstructured Grids Patrice Castonguay and Antony Jameson Aerospace Computing Lab, Stanford University GTC Asia, Beijing, China December 15 th, 2011
Contribution to GMGW-1
Contribution to GMGW-1 Vivek Ahuja, Shaunak Pai, John Wilson, Rajesh Kumar, Michael Stubert Inc. (003) Restricted Siemens AG 2017 Realize innovation. Summary of meshes generated Star-CCM+ Geometry Core
State of the art at DLR in solving aerodynamic shape optimization problems using the discrete viscous adjoint method
DLR - German Aerospace Center State of the art at DLR in solving aerodynamic shape optimization problems using the discrete viscous adjoint method J. Brezillon, C. Ilic, M. Abu-Zurayk, F. Ma, M. Widhalm
10.1 Overview. Section 10.1: Overview. Section 10.2: Procedure for Generating Prisms. Section 10.3: Prism Meshing Options
Chapter 10. Generating Prisms This chapter describes the automatic and manual procedure for creating prisms in TGrid. It also discusses the solution to some common problems that you may face while creating
A DRAG PREDICTION VALIDATION STUDY FOR AIRCRAFT AERODYNAMIC ANALYSIS
A DRAG PREDICTION VALIDATION STUDY FOR AIRCRAFT AERODYNAMIC ANALYSIS Akio OCHI, Eiji SHIMA Kawasaki Heavy Industries, ltd Keywords: CFD, Drag prediction, Validation Abstract A CFD drag prediction validation
Introduction to ANSYS CFX
Workshop 03 Fluid flow around the NACA0012 Airfoil 16.0 Release Introduction to ANSYS CFX 2015 ANSYS, Inc. March 13, 2015 1 Release 16.0 Workshop Description: The flow simulated is an external aerodynamics
GEOMETRY MODELING & GRID GENERATION
GEOMETRY MODELING & GRID GENERATION Dr.D.Prakash Senior Assistant Professor School of Mechanical Engineering SASTRA University, Thanjavur OBJECTIVE The objectives of this discussion are to relate experiences
Contribution to GMGW 1
Contribution to GMGW 1 Rocco Nastasia, Saurabh Tendulkar, Mark Beall Simmetrix Inc., Clifton Park, NY 12065 Riccardo Balin, Scott Wurst, Ryan Skinner, Kenneth E. Jansen Department of Aerospace Engineering
Aerodynamic optimization using Adjoint methods and parametric CAD models
Aerodynamic optimization using Adjoint methods and parametric CAD models ECCOMAS Congress 2016 P. Hewitt S. Marques T. Robinson D. Agarwal @qub.ac.uk School of Mechanical and Aerospace Engineering Queen
CAD-BASED WORKFLOWS. VSP Workshop 2017
CAD-BASED WORKFLOWS VSP Workshop 2017 RESEARCH IN FLIGHT COMPANY Established 2012 Primary functions are the development, marketing and support of FlightStream and the development of aerodynamic solutions
NUMERICAL 3D TRANSONIC FLOW SIMULATION OVER A WING
Review of the Air Force Academy No.3 (35)/2017 NUMERICAL 3D TRANSONIC FLOW SIMULATION OVER A WING Cvetelina VELKOVA Department of Technical Mechanics, Naval Academy Nikola Vaptsarov,Varna, Bulgaria (cvetelina.velkova1985@gmail.com)
ANSYS ICEM CFD User's Manual
ANSYS ICEM CFD User's Manual ANSYS, Inc. Southpointe 2600 ANSYS Drive Canonsburg, PA 15317 ansysinfo@ansys.com http://www.ansys.com (T) 724-746-3304 (F) 724-514-9494 Release 17.0 January 2016 ANSYS, Inc.
Multigrid Solvers in CFD. David Emerson. Scientific Computing Department STFC Daresbury Laboratory Daresbury, Warrington, WA4 4AD, UK
Multigrid Solvers in CFD David Emerson Scientific Computing Department STFC Daresbury Laboratory Daresbury, Warrington, WA4 4AD, UK david.emerson@stfc.ac.uk 1 Outline Multigrid: general comments Incompressible
UNSTRUCTURED MESH CAPABILITES FOR SUPERSONIC WING DESIGN AT LOW SPEED CONDITIONS
CFD & OPTIMIZATION 2011-048 An ECCOMAS Thematic Conference 23-25 May 2011, Antalya TURKEY UNSTRUCTURED MESH CAPABILITES FOR SUPERSONIC WING DESIGN AT LOW SPEED CONDITIONS Michele Gaffuri, Joël Brezillon
15. SAILBOAT GEOMETRY
SAILBOAT GEOMETRY 15. SAILBOAT GEOMETRY In this tutorial you will import a STEP file that describes the geometry of a sailboat hull. You will split the hull along the symmetry plane, create a flow volume
Geometry Vocabulary. acute angle-an angle measuring less than 90 degrees
Geometry Vocabulary acute angle-an angle measuring less than 90 degrees angle-the turn or bend between two intersecting lines, line segments, rays, or planes angle bisector-an angle bisector is a ray that
Studies of the Continuous and Discrete Adjoint Approaches to Viscous Automatic Aerodynamic Shape Optimization
Studies of the Continuous and Discrete Adjoint Approaches to Viscous Automatic Aerodynamic Shape Optimization Siva Nadarajah Antony Jameson Stanford University 15th AIAA Computational Fluid Dynamics Conference
Algorithmic Developments in TAU
Algorithmic Developments in TAU Ralf Heinrich, Richard Dwight, Markus Widhalm, and Axel Raichle DLR Institute of Aerodynamics and Flow Technology, Lilienthalplatz 7, 38108, Germany ralf.heinrich@dlr.de,
AIR LOAD CALCULATION FOR ISTANBUL TECHNICAL UNIVERSITY (ITU), LIGHT COMMERCIAL HELICOPTER (LCH) DESIGN ABSTRACT
AIR LOAD CALCULATION FOR ISTANBUL TECHNICAL UNIVERSITY (ITU), LIGHT COMMERCIAL HELICOPTER (LCH) DESIGN Adeel Khalid *, Daniel P. Schrage + School of Aerospace Engineering, Georgia Institute of Technology
Structured Grid Generation for Turbo Machinery Applications using Topology Templates
Structured Grid Generation for Turbo Machinery Applications using Topology Templates January 13th 2011 Martin Spel martin.spel@rtech.fr page 1 Agenda: R.Tech activities Grid Generation Techniques Structured
Geometry Parameterization for Shape Optimization. Arno Ronzheimer
Geometry Parameterization for Shape Optimization Arno Ronzheimer Dokumentname > 11.07.2006 23.11.2004 Overview Motivation for Geometry Parameterization Classification of Methods Criteria for Choosing a
SHOCK WAVES IN A CHANNEL WITH A CENTRAL BODY
SHOCK WAVES IN A CHANNEL WITH A CENTRAL BODY A. N. Ryabinin Department of Hydroaeromechanics, Faculty of Mathematics and Mechanics, Saint-Petersburg State University, St. Petersburg, Russia E-Mail: a.ryabinin@spbu.ru
CFD Methods for Aerodynamic Design
CFD Methods for Aerodynamic Design Afandi Darlington Optimal Aerodynamics Ltd Why CFD? Datasheet methods are still very relevant today (ESDU, USAF DATCOM) Validated estimates of lift, drag, moments, stability
Case 3.1: Turbulent Flow over a 2D Multi-Element Airfoil. Summary of Results. Marco Ceze
Case 3.1: Turbulent Flow over a 2D Multi-Element Airfoil Summary of Results Marco Ceze (mceze@umich.edu) 2 nd International Workshop on High-Order CFD Methods, May 27-28, Cologne, Germany C3.1 1/14 Case
Debojyoti Ghosh. Adviser: Dr. James Baeder Alfred Gessow Rotorcraft Center Department of Aerospace Engineering
Debojyoti Ghosh Adviser: Dr. James Baeder Alfred Gessow Rotorcraft Center Department of Aerospace Engineering To study the Dynamic Stalling of rotor blade cross-sections Unsteady Aerodynamics: Time varying
ABOUT THE GENERATION OF UNSTRUCTURED MESH FAMILIES FOR GRID CONVERGENCE ASSESSMENT BY MIXED MESHES
VI International Conference on Adaptive Modeling and Simulation ADMOS 2013 J. P. Moitinho de Almeida, P. Díez, C. Tiago and N. Parés (Eds) ABOUT THE GENERATION OF UNSTRUCTURED MESH FAMILIES FOR GRID CONVERGENCE
Workshop 3: Cutcell Mesh Generation. Introduction to ANSYS Fluent Meshing Release. Release ANSYS, Inc.
Workshop 3: Cutcell Mesh Generation 14.5 Release Introduction to ANSYS Fluent Meshing 1 2011 ANSYS, Inc. December 21, 2012 I Introduction Workshop Description: CutCell meshing is a general purpose meshing
Introduction to CFX. Workshop 2. Transonic Flow Over a NACA 0012 Airfoil. WS2-1. ANSYS, Inc. Proprietary 2009 ANSYS, Inc. All rights reserved.
Workshop 2 Transonic Flow Over a NACA 0012 Airfoil. Introduction to CFX WS2-1 Goals The purpose of this tutorial is to introduce the user to modelling flow in high speed external aerodynamic applications.
Application of Wray-Agarwal Turbulence Model for Accurate Numerical Simulation of Flow Past a Three-Dimensional Wing-body
Washington University in St. Louis Washington University Open Scholarship Mechanical Engineering and Materials Science Independent Study Mechanical Engineering & Materials Science 4-28-2016 Application
Unstructured Mesh Related Issues In Computational Fluid Dynamics (CFD) Based Analysis And Design
Unstructured Mesh Related Issues In Computational Fluid Dynamics (CFD) Based Analysis And Design Dimitri J. Mavriplis ICASE NASA Langley Research Center Hampton, VA 23681 USA 11 th International Meshing
German Aerospace Center, Institute of Aerodynamics and Flow Technology, Numerical Methods
Automatische Transitionsvorhersage im DLR TAU Code Status der Entwicklung und Validierung Automatic Transition Prediction in the DLR TAU Code - Current Status of Development and Validation Andreas Krumbein
The Numerical Simulation of Civil Transportation High-lift Configuration
Available online at www.sciencedirect.com ScienceDirect Procedia Engineering 00 (2014) 000 000 www.elsevier.com/locate/procedia APISAT2014, 2014 Asia-Pacific International Symposium on Aerospace Technology,
An Investigation of Directional-Coarsening And Line-Implicit Smoothing Applied to Agglomeration Multigrid
An Investigation of Directional-Coarsening And Line-Implicit Smoothing Applied to Agglomeration Multigrid J. V. Lassaline Ryerson University 35 Victoria St, Toronto, ON, M5B 2K3, Canada D. W. Zingg University
Shrinkwrap developments for computational electromagnetics in ICE NITe
Shrinkwrap developments for computational electromagnetics in ICE NITe Preparing CAD models for electromagnetic analysis remains a complex, time consuming process. Typically, the CAD model will contain
Lecture 6: CAD Import Release. Introduction to ANSYS Fluent Meshing
Lecture 6: CAD Import 14.5 Release Introduction to ANSYS Fluent Meshing 1 Fluent Meshing 14.5 Assembly meshing Workflow This Lecture Tessellated or Conformal CAD import Cap Inlet/Outlets, Create Domains/BOI
Free Convection Cookbook for StarCCM+
ME 448/548 February 28, 2012 Free Convection Cookbook for StarCCM+ Gerald Recktenwald gerry@me.pdx.edu 1 Overview Figure 1 depicts a two-dimensional fluid domain bounded by a cylinder of diameter D. Inside
Topological Issues in Hexahedral Meshing
Topological Issues in Hexahedral Meshing David Eppstein Univ. of California, Irvine Dept. of Information and Computer Science Outline I. What is meshing? Problem statement Types of mesh Quality issues
5. Release Notes - Version 15
Gridgen Version 15.18 - Release Date: August 2012 5. Release Notes - Version 15 5.1 Gridgen Version 15.18 - Release Date: August 2012 The following is a list of new features included in V15.18: 1. Improvements
Express Introductory Training in ANSYS Fluent Workshop 04 Fluid Flow Around the NACA0012 Airfoil
Express Introductory Training in ANSYS Fluent Workshop 04 Fluid Flow Around the NACA0012 Airfoil Dimitrios Sofialidis Technical Manager, SimTec Ltd. Mechanical Engineer, PhD PRACE Autumn School 2013 -
A GRAPHICALLY INTERACTIVE APPROACH TO STRUCTURED AND UNSTRUCTURED SURFACE GRID QUALITY ANALYSIS. John E. Stewart * Jamshid S.
A GRAPHICALLY INTERACTIVE APPROACH TO STRUCTURED AND UNSTRUCTURED SURFACE GRID QUALITY ANALYSIS John E. Stewart * Jamshid S. Abolhassani Abstract A graphically interactive approach to structured and unstructured
Computational Fluid Dynamics for Engineers
Tuncer Cebeci Jian P. Shao Fassi Kafyeke Eric Laurendeau Computational Fluid Dynamics for Engineers From Panel to Navier-Stokes Methods with Computer Programs With 152 Figures, 19 Tables, 84 Problems and
Verification of Moving Mesh Discretizations
Verification of Moving Mesh Discretizations Krzysztof J. Fidkowski High Order CFD Workshop Kissimmee, Florida January 6, 2018 How can we verify moving mesh results? Goal: Demonstrate accuracy of flow solutions
Introduction to ANSYS ICEM CFD
Lecture 4 Volume Meshing 14. 0 Release Introduction to ANSYS ICEM CFD 1 2011 ANSYS, Inc. March 21, 2012 Introduction to Volume Meshing To automatically create 3D elements to fill volumetric domain Generally
The Quality Of 3D Models
The Quality Of 3D Models Problems and Solutions for Applications Post-Design Fathi El-Yafi Senior Product Engineer Product Department of EXA Corporation 1 : Overview Status Problems Identified Defect Sources
Development of mesh refinement methods at CFD codes for computational fluid mechanics problems DIPLOMA THESIS
NATIONAL TECHNICAL UNIVERSITY OF ATHENS DEPARTMENT OF MECHANICAL ENGINEERING SECTION OF FLUID MECHANICS Development of mesh refinement methods at CFD codes for computational fluid mechanics problems DIPLOMA
Finite Element Flow Simulations of the EUROLIFT DLR-F11 High Lift Configuration
Finite Element Flow Simulations of the EUROLIFT DLR-F11 High Lift Configuration Kedar C. Chitale MANE Dept., Rensselaer Polytechnic Institute, NY 12180 Michel Rasquin Leadership Computing Facility, Argonne
Introduction to ANSYS FLUENT Meshing
Workshop 02 Volume Fill Methods Introduction to ANSYS FLUENT Meshing 1 2011 ANSYS, Inc. December 21, 2012 I Introduction Workshop Description: Mesh files will be read into the Fluent Meshing software ready
The use of gas-kinetic schemes for the simulation of compressible flows become widespread in the two last
A Gas-Kinetic BGK Scheme for Parallel Solution of 3-D Viscous Flows on Unstructured Hybrid Grids Murat Ilgaz Defense Industries Research and Development Institute, Ankara, 626, Turkey and Ismail H. Tuncer
EXPLICIT AND IMPLICIT TVD AND ENO HIGH RESOLUTION ALGORITHMS APPLIED TO THE EULER AND NAVIER-STOKES EQUATIONS IN THREE-DIMENSIONS RESULTS
EXPLICIT AND IMPLICIT TVD AND ENO HIGH RESOLUTION ALGORITHMS APPLIED TO THE EULER AND NAVIER-STOKES EQUATIONS IN THREE-DIMENSIONS RESULTS Edisson Sávio de Góes Maciel, edissonsavio@yahoo.com.br Mechanical
Modeling External Compressible Flow
Tutorial 3. Modeling External Compressible Flow Introduction The purpose of this tutorial is to compute the turbulent flow past a transonic airfoil at a nonzero angle of attack. You will use the Spalart-Allmaras
MULTI-OBJECTIVE OPTIMISATION IN MODEFRONTIER FOR AERONAUTIC APPLICATIONS
EVOLUTIONARY METHODS FOR DESIGN, OPTIMIZATION AND CONTROL P. Neittaanmäki, J. Périaux and T. Tuovinen (Eds.) CIMNE, Barcelona, Spain 2007 MULTI-OBJECTIVE OPTIMISATION IN MODEFRONTIER FOR AERONAUTIC APPLICATIONS
NUMERICAL SIMULATIONS OF TURBULENT FLOWS OVER THE ONERA-M6 AND DLR-F6 CONFIGURATIONS
NUMERICAL SIMULATIONS OF TURBULENT FLOWS OVER THE ONERA-M6 AND DLR-F6 CONFIGURATIONS Ricardo Galdino da Silva, João Luiz F. Azevedo Instituto de Aeronáutica e Espaço, DCTA/IAE/ALA, São José dos Campos,
CGT 581 G Geometric Modeling Surfaces (part I)
CGT 581 G Geometric Modeling Surfaces (part I) Bedrich Benes, Ph.D. Purdue University Department of Computer Graphics Technology Polygonal Representation The common representation is a mesh of triangles
Abstract. Introduction
EULER SOLUTIONS AS LIMIT OF INFINITE REYNOLDS NUMBER FOR SEPARATION FLOWS AND FLOWS WITH VORTICES Wolfgang Schmidt and Antony Jameson Dornier GmbH, D-7990 Friedrichshafen, FRG and Princeton University,
Coupling of STAR-CCM+ to Other Theoretical or Numerical Solutions. Milovan Perić
Coupling of STAR-CCM+ to Other Theoretical or Numerical Solutions Milovan Perić Contents The need to couple STAR-CCM+ with other theoretical or numerical solutions Coupling approaches: surface and volume
simulations to capture boundary layers efficiently with semi-structured elements or anisotropic, rightangled tetrahedra. The unstructured meshes can b
Challenges in Unstructured Mesh Generation for Practical and Efficient Computational Fluid Dynamics Simulations Yasushi Ito a,* a Japan Aerospace Exploration Agency (JAXA), 6-13-1 Osawa, Mitaka, Tokyo
X-31A VECTOR High Angle of Attack Descent Euler and Navier-Stokes Simulations of Unsteady Manoeuvres
X-31A VECTOR High Angle of Attack Descent Euler and Navier-Stokes Simulations of Unsteady Manoeuvres Stephan M. Hitzel, Edwin van der Weide, Udo Tremel, Herbert Rieger Numerical Flow Simulation, EADS Military
Unstructured Grid Generation Using Automatic Point Insertion and Local Reconnection
18 Unstructured Grid Generation Using Automatic Point Insertion and Local Reconnection David L. Marcum 18.1 Introduction 18.2 Unstructured Grid Generation Procedure 18.3 Two-Dimensional Application Examples
TGrid 5.0 Tutorial Guide
TGrid 5.0 Tutorial Guide April 2008 Copyright c 2008 by ANSYS, Inc. All Rights Reserved. No part of this document may be reproduced or otherwise used in any form without express written permission from
Geometry Definition in the ADINA User Interface (AUI) Daniel Jose Payen, Ph.D. March 7, 2016
Geometry Definition in the ADINA User Interface (AUI) Daniel Jose Payen, Ph.D. March 7, 2016 ADINA R&D, Inc., 2016 1 Topics Presented ADINA에서쓰이는 Geometry 종류 Simple (AUI) geometry ADINA-M geometry ADINA-M
Best Practices: Volume Meshing Kynan Maley
Best Practices: Volume Meshing Kynan Maley Volume Meshing Volume meshing is the basic tool that allows the creation of the space discretization needed to solve most of the CAE equations for: CFD Stress
Fully Automated, Parallel and Topology Agnostic Domain Connectivity For Overlapping Surface Meshes Fields
Overset and Composite Grid Symposium, University of Maryland Oct 1-3, 2018 Fully Automated, Parallel and Topology Agnostic Domain Connectivity For Overlapping Surface Meshes Fields Approved for public
Calypso Construction Features. Construction Features 1
Calypso 1 The Construction dropdown menu contains several useful construction features that can be used to compare two other features or perform special calculations. Construction features will show up
Strömningslära Fluid Dynamics. Computer laboratories using COMSOL v4.4
UMEÅ UNIVERSITY Department of Physics Claude Dion Olexii Iukhymenko May 15, 2015 Strömningslära Fluid Dynamics (5FY144) Computer laboratories using COMSOL v4.4!! Report requirements Computer labs must
The gas-kinetic methods have become popular for the simulation of compressible fluid flows in the last
Parallel Implementation of Gas-Kinetic BGK Scheme on Unstructured Hybrid Grids Murat Ilgaz Defense Industries Research and Development Institute, Ankara, 626, Turkey and Ismail H. Tuncer Middle East Technical
Validation of an Unstructured Overset Mesh Method for CFD Analysis of Store Separation D. Snyder presented by R. Fitzsimmons
Validation of an Unstructured Overset Mesh Method for CFD Analysis of Store Separation D. Snyder presented by R. Fitzsimmons Stores Separation Introduction Flight Test Expensive, high-risk, sometimes catastrophic
Best Practices for Aerospace Aerodynamics. Peter Ewing
Best Practices for Aerospace Aerodynamics Peter Ewing Agenda Pre-processing Geometry Origin/Import Geometry Prep Surface Mesh Volume Mesh Solver Settings Defining Flight Physics Setting Up Solvers Post-processing
DISCONTINUOUS FINITE ELEMENT VISUALIZATION
1 1 8th International Symposium on Flow Visualisation (1998) DISCONTINUOUS FINITE ELEMENT VISUALIZATION A. O. Leone P. Marzano E. Gobbetti R. Scateni S. Pedinotti Keywords: visualization, high-order finite
TAU User Meeting, Göttingen,
TAU User Meeting, Göttingen, 22.9.2005 Fluid-Structure-Coupling Using the TAU Code: Developments and Applications at the DLR Institute of Aeroelasticity Wolf Krüger DLR Institute of Aeroelasticity Fluid-Structure-Coupling
Tutorial 2. Modeling Periodic Flow and Heat Transfer
Tutorial 2. Modeling Periodic Flow and Heat Transfer Introduction: Many industrial applications, such as steam generation in a boiler or air cooling in the coil of an air conditioner, can be modeled as
FEMLAB Exercise 1 for ChE366
FEMLAB Exercise 1 for ChE366 Problem statement Consider a spherical particle of radius r s moving with constant velocity U in an infinitely long cylinder of radius R that contains a Newtonian fluid. Let
Comparisons of Compressible and Incompressible Solvers: Flat Plate Boundary Layer and NACA airfoils
Comparisons of Compressible and Incompressible Solvers: Flat Plate Boundary Layer and NACA airfoils Moritz Kompenhans 1, Esteban Ferrer 2, Gonzalo Rubio, Eusebio Valero E.T.S.I.A. (School of Aeronautics)
Verification and Validation of Turbulent Flow around a Clark-Y Airfoil
Verification and Validation of Turbulent Flow around a Clark-Y Airfoil 1. Purpose 58:160 Intermediate Mechanics of Fluids CFD LAB 2 By Tao Xing and Fred Stern IIHR-Hydroscience & Engineering The University
AERODYNAMIC DESIGN OF FLYING WING WITH EMPHASIS ON HIGH WING LOADING
AERODYNAMIC DESIGN OF FLYING WING WITH EMPHASIS ON HIGH WING LOADING M. Figat Warsaw University of Technology Keywords: Aerodynamic design, CFD Abstract This paper presents an aerodynamic design process
Module D: Laminar Flow over a Flat Plate
Module D: Laminar Flow over a Flat Plate Summary... Problem Statement Geometry and Mesh Creation Problem Setup Solution. Results Validation......... Mesh Refinement.. Summary This ANSYS FLUENT tutorial
An Optimization Method Based On B-spline Shape Functions & the Knot Insertion Algorithm
An Optimization Method Based On B-spline Shape Functions & the Knot Insertion Algorithm P.A. Sherar, C.P. Thompson, B. Xu, B. Zhong Abstract A new method is presented to deal with shape optimization problems.
Supporting planning for shape, space and measures in Key Stage 4: objectives and key indicators
1 of 7 Supporting planning for shape, space and measures in Key Stage 4: objectives and key indicators This document provides objectives to support planning for shape, space and measures in Key Stage 4.
Pick up some wrapping paper.
Pick up some wrapping paper. What is the area of the following Christmas Tree? There is a nice theorem that allows one to compute the area of any simply-connected (i.e. no holes) grid polygon quickly.
High-Lift Aerodynamics: STAR-CCM+ Applied to AIAA HiLiftWS1 D. Snyder
High-Lift Aerodynamics: STAR-CCM+ Applied to AIAA HiLiftWS1 D. Snyder Aerospace Application Areas Aerodynamics Subsonic through Hypersonic Aeroacoustics Store release & weapons bay analysis High lift devices
Numerical and Mesh Resolution Requirements for. Accurate Sonic Boom Prediction of Complete Aircraft. configurations.
Numerical and Mesh Resolution Requirements for Accurate Sonic Boom Prediction of Complete Aircraft Configurations S. Choi, J. J. Alonso, and E. Van der Weide Department of Aeronautics & Astronautics Stanford
Introduction to C omputational F luid Dynamics. D. Murrin
Introduction to C omputational F luid Dynamics D. Murrin Computational fluid dynamics (CFD) is the science of predicting fluid flow, heat transfer, mass transfer, chemical reactions, and related phenomena
AN ADAPTIVE UNSTRUCTURED GRID METHOD BY GRID SUBDIVISION, LOCAL REMESHING, AND GRID MOVEMENT
AIAA AIAA 99 3255 AN ADAPTIVE UNSTRUCTURED GRID METHOD BY GRID SUBDIVISION, LOCAL REMESHING, AND GRID MOVEMENT S.Z. Pirzadeh Configuration Aerodynamics Branch MS 499, NASA Langley Research Center Hampton,
AIAA A Computational Study of Subsonic Flows over A Medium Range Cargo Aircraft
S AIAA 23-366 A Computational Study of Subsonic Flows over A Medium Range Cargo Aircraft 2st Applied Aerodynamic Conference 23-26 June 23 Orlando, Florida For permission to copy or to republish, contact
The Spalart Allmaras turbulence model
The Spalart Allmaras turbulence model The main equation The Spallart Allmaras turbulence model is a one equation model designed especially for aerospace applications; it solves a modelled transport equation
Introduction to ANSYS FLUENT Meshing
Workshop 04 CAD Import and Meshing from Conformal Faceting Input 14.5 Release Introduction to ANSYS FLUENT Meshing 2011 ANSYS, Inc. December 21, 2012 1 I Introduction Workshop Description: CAD files will
Optimate CFD Evaluation Optimate Glider Optimization Case
Optimate CFD Evaluation Optimate Glider Optimization Case Authors: Nathan Richardson LMMFC CFD Lead 1 Purpose For design optimization, the gold standard would be to put in requirements and have algorithm
2D mesh generation using DeViSoR Grid and GiD
2D mesh generation using DeViSoR Grid and GiD Dipl.-Math. Jens Friedrich Acker Dipl.-Inform. (FH) Thomas Rohkämper Mathematics III: Applied Mathematics and Numerics TU Dortmund University Oct. 28, 2010
acute angle An angle with a measure less than that of a right angle. Houghton Mifflin Co. 2 Grade 5 Unit 6
acute angle An angle with a measure less than that of a right angle. Houghton Mifflin Co. 2 Grade 5 Unit 6 angle An angle is formed by two rays with a common end point. Houghton Mifflin Co. 3 Grade 5 Unit
High-order methods for the next generation of computational engineering software
High-order methods for the next generation of computational engineering software Rubén Sevilla Zienkiewicz Centre for Computational Engineering College of Engineering Swansea University Swansea Wales,
Repairing a Boundary Mesh
Tutorial 1. Repairing a Boundary Mesh Introduction TGrid offers several tools for mesh repair. While there is no right or wrong way to repair a mesh, the goal is to improve the quality of the mesh with
CATIA V5-6R2015 Product Enhancement Overview
Click to edit Master title style CATIA V5-6R2015 Product Enhancement Overview John Montoya, PLM Technical Support March 2015 1 2010 Inceptra LLC. All rights reserved. Overview of Enhanced Products Overview
Generating Airplane Wings for Numerical Simulation and Manufacturing
Generating Airplane Wings for Numerical Simulation and Manufacturing Karl-Heinz Brakhage Philipp Lamby Institute of Geometry and Applied Mathematics RWTH Aachen, University of Technology D-52056 Aachen,
Learning from Home Activity Booklet
Year 2 Maths Geometry Properties of Shapes Learning from Home Activity Booklet Year 2 Programme of Study Statistics Statutory requirements Activity Sheet Page Number Notes Identify and describe the properties