CFD simulations of flow over NASA Trap Wing Model
|
|
|
- Gregory Tracy West
- 9 years ago
- Views:
Transcription
1 CFD simulations of flow over NASA Trap Wing Model Andy Luo Swift Engineering Pravin Peddiraju, Vangelis Skaperdas BETA CAE Systems
2 Introduction A cooperative study was undertaken by BETA and Swift Engineering to participate in the AIAA High Lift Prediction Workshop. Preliminary data were presented at the meeting. The study was continued after the meeting, and data were obtained on improved grids. Also, an additional turbulence model was run for the baseline configuration. This presentation contains the updated data on the new grids as well as the additional turbulence model data. June st High Lift Prediction Workshop 2
3 Overview ANSA, a commercial CAE pre-processing software from BETA CAE Systems, was used for grid generation. CFD++, a commercial CFD solver from METACOMP technologies, was used for numerical simulations. Realizable k-epsilon turbulence model was used for Turbulence modeling. Flow Conditions: Mach = 0.2 Reynolds Number 4.3e6 based on MAC MAC of in Reference Temp of 520 R Cases Studied: Case 1: Grid Convergence Angles-of-attack at 13 degrees and 28 degrees Case 2: Flap Deflection Prediction Study Flap deflection of 25 degrees and 20 degrees June st High Lift Prediction Workshop 3
4 Grids Statistics Config-1 Config-8 Coarse Medium Fine Medium Field Nodes 3,438,517 11,339,107 36,890,922 11,401,724 Field Cells 10,697,988 30,785,946 91,675,985 30,954,927 Boundary Nodes 200, ,115 1,016, ,604 Boundary Faces 397, ,186 2,015, ,164 Boundary Layer, First height 2e-4" 1.3e-4" 9e-5" 1.3e-4" June st High Lift Prediction Workshop 4
5 Size Boxes Multiple size boxes were created to refine surface and volume mesh at critical areas such as body nose, wing-body intersection, wing-tips etc., without splitting the original domain June st High Lift Prediction Workshop 5
6 Meshing Automation Batch Meshing tool was used to automate all the meshing steps: 1) Surface Meshing, 2) Boundary Layer generation, and 3) Volume Meshing. Once the Batch Mesh frame work was defined for coarse mesh for Config1, the mesh parameter values were appropriately scaled to generate medium and fine meshes. The frame work for Config1 medium mesh was directly used to generate consistent mesh for Config8 medium mesh case. June st High Lift Prediction Workshop 6
7 Grids Surface Mesh Coarse June st High Lift Prediction Workshop 7
8 Grids Surface Mesh Medium June st High Lift Prediction Workshop 8
9 Grids Surface Mesh Fine June st High Lift Prediction Workshop 9
10 Grids Volume Mesh Coarse Mid span cross-section June st High Lift Prediction Workshop 10
11 Grids Volume Mesh Medium Coarse Mid span cross-section June st High Lift Prediction Workshop 11
12 Grids Volume Mesh Fine Mid span cross-section June st High Lift Prediction Workshop 12
13 Case 1: Grid Convergence Study Alpha = 13 degrees Cell Count CL CD CM Coarse 10,697, Medium 30,785, Fine 91,675, June st High Lift Prediction Workshop 13
14 Case 1: Grid Convergence Study Alpha = 28 degrees Cell Count CL CD CM Coarse 10,697, Medium 30,785, Fine 91,675, June st High Lift Prediction Workshop 14
15 Case 1: Grid Convergence Study Alpha = 13 degrees Alpha = 28 degrees Grid Convergence Alpha 13 Grid Convergence Alpha CL CL Exp CD CD Exp CL CL Exp CD CD Exp CL CD CL CD N^(-2/3) N^(-2/3) June st High Lift Prediction Workshop 15
16 Case 1: Grid Convergence Study Lift Curve Experimental Data (Config 1) Coa rs e Medium Fine CL Alpha June st High Lift Prediction Workshop 16
17 Case 1: Grid Convergence Study Drag Curve Experimental Data (Config 1) Coa rs e Medium Fine CD Alpha June st High Lift Prediction Workshop 17
18 Case 1: Grid Convergence Study Drag Polar Experimental Data (Config 1) Coa rs e Medium Fine CL C D June st High Lift Prediction Workshop 18
19 Case 1: Grid Convergence Study Moment Curve Experimental Data (Config 1) Coa rs e Medium Fine -0.2 CM Alpha June st High Lift Prediction Workshop 19
20 Case 2: Flap Deflection Prediction Study Configuration 1:Flap 25 degrees Alpha CL CD CM Configuration 8:Flap 20 degrees Alpha CL CD CM June st High Lift Prediction Workshop 20
21 Case 2: Flap Deflection Prediction Study Lift Curve Experimental Data (Config 1) Experimental Data (Config 8) Medium (Config 1) Medium (Config 8) CL Alpha June st High Lift Prediction Workshop 21
22 Case 2: Flap Deflection Prediction Study Drag Curve Experimental Data (Config 1) Experimental Data (Config 8) Medium (Config 1) Medium (Config 8) CD Alpha June st High Lift Prediction Workshop 22
23 Case 2: Flap Deflection Prediction Study Moment Curve Experimental Data (Config 1) Experimental Data (Config 8) Medium (Config 1) Medium (Config 8) -0.2 CM Alpha June st High Lift Prediction Workshop 23
24 Case 2: Flap Deflection Prediction Study Coarse Medium Fine a13 a28 June st High Lift Prediction Workshop 24
25 Body Pod Flow Reversal: Case 2 Medium Fine a13 a28 June st High Lift Prediction Workshop 25
26 Flap Separation: Case 1 Coarse Medium Fine a13 a28 June st High Lift Prediction Workshop 26
27 Flap Separation: Case 2 Medium Fine a13 a28 June st High Lift Prediction Workshop 27
28 Flow Confluence: Coarse MidSpan Tip a13 a28 June st High Lift Prediction Workshop 28
29 Flow Confluence: Medium MidSpan Tip a13 a28 June st High Lift Prediction Workshop 29
30 Flow Confluence: Fine MidSpan Tip a13 a28 June st High Lift Prediction Workshop 30
31 Flow Confluence: Stowed Medium MidSpan Tip a13 a28 June st High Lift Prediction Workshop 31
32 Turbulence Model Study Lift Curve Experimental Data (Config 1) Medium ke Medium SA 2 CL Alpha June st High Lift Prediction Workshop 32
33 Turbulence Model Study Drag Curve Experimental Data (Config 1) Medium ke Medium SA CD Alpha June st High Lift Prediction Workshop 33
34 Turbulence Model Study Drag Polar Experimental Data (Config 1) Medium ke Medium SA CL C D June st High Lift Prediction Workshop 34
35 Turbulence Model Study Moment Curve 0 Experimental Data (Config 1) -0.1 Medium ke Medium SA -0.2 CM Alpha June st High Lift Prediction Workshop 35
36 Summary Cooperative effort between Swift Engineering and BETA CAE Systems 100 Million cell limit is a very tight constraint for High Lift Prediction Solution was path dependent Restart from previous alpha is preferable Solution was grid dependent Improved correlation on revised grids Solution was turbulence model dependent Realizable K-Epsilon Model under-predicted CLmax relative to Spalart Allmaras model on the same grid Realizable K-Epsilon Model did a better job of predicting the stall angle than Spalart Allmaras on the same grid. Medium Grid level begins to accurately capture flow phenomenon Flap Side of Body separation Confluent Boundary Layers Grid convergence at lower angles was reasonable Grid convergence not achieved at angles close to CLmax June st High Lift Prediction Workshop 36
37 Conclusions on Revised Study Initial grid effort resulted in poor correlation with experimental data Larger grids yet poorer convergence Key areas too coarse (e.g., Leading Edge Regions) Revised grids showed better correlation with experimental data Fewer prism layers Refinement on the surface as well as Slat and Flap gaps Lower cell count in Coarse and Medium grids Results still under-predicted CLmax region June st High Lift Prediction Workshop 37
38 Conclusions on Revised Study Grid refinement study emphasized importance of proper grid modeling to obtain good correlation Results presented by Metacomp at the workshop using CFD++ on AIAA provided grids with the Spalart Allmaras turbulence model showed slightly better correlation with the experimental data than those obtained in this study with Spalart Allmaras Further grid refinements could improve correlation Realizable K-Epsilon turbulence model was likely not the proper choice Spalart Allmaras correlation was better than Realizable K-Epsilon Metacomp s workshop results using CFD++ with the K-Epsilon RT model showed noticeably better correlation with the experimental data than the Realizable K-Epsilon results presented in this study K-Epsilon RT model should be investigated June st High Lift Prediction Workshop 38
39 Proposed Future Work Run AIAA provided grids for comparison Refine grids further Investigate other turbulence models such as K-Epsilon RT June st High Lift Prediction Workshop 39
The influence of mesh characteristics on OpenFOAM simulations of the DrivAer model
The influence of mesh characteristics on OpenFOAM simulations of the DrivAer model Vangelis Skaperdas, Aristotelis Iordanidis, Grigoris Fotiadis BETA CAE Systems S.A. 2 nd Northern Germany OpenFOAM User
XFlow CFD results for the 1st AIAA High Lift Prediction Workshop
XFlow CFD results for the 1st AIAA High Lift Prediction Workshop David M. Holman, Dr. Monica Mier-Torrecilla, Ruddy Brionnaud Next Limit Technologies, Spain THEME Computational Fluid Dynamics KEYWORDS
Computational Simulation of Flow Over a High-Lift Trapezoidal Wing
Computational Simulation of Flow Over a High-Lift Trapezoidal Wing Abhishek Khare a,1, Raashid Baig a, Rajesh Ranjan a, Stimit Shah a, S Pavithran a, Kishor Nikam a,1, Anutosh Moitra b a Computational
A. Hyll and V. Horák * Department of Mechanical Engineering, Faculty of Military Technology, University of Defence, Brno, Czech Republic
AiMT Advances in Military Technology Vol. 8, No. 1, June 2013 Aerodynamic Characteristics of Multi-Element Iced Airfoil CFD Simulation A. Hyll and V. Horák * Department of Mechanical Engineering, Faculty
Aerodynamic Design Optimization Discussion Group Case 4: Single- and multi-point optimization problems based on the CRM wing
Aerodynamic Design Optimization Discussion Group Case 4: Single- and multi-point optimization problems based on the CRM wing Lana Osusky, Howard Buckley, and David W. Zingg University of Toronto Institute
CFD Analysis of Civil Transport Aircraft
IJSRD - International Journal for Scientific Research & Development Vol. 3, Issue 06, 2015 ISSN (online): 2321-0613 CFD Analysis of Civil Transport Aircraft Parthsarthi A Kulkarni 1 Dr. Pravin V Honguntikar
C3.8 CRM wing/body Case
C3.8 CRM wing/body Case 1. Code description XFlow is a high-order discontinuous Galerkin (DG) finite element solver written in ANSI C, intended to be run on Linux-type platforms. Relevant supported equation
THE CFD SIMULATION OF THE FLOW AROUND THE AIRCRAFT USING OPENFOAM AND ANSA
THE CFD SIMULATION OF THE FLOW AROUND THE AIRCRAFT USING OPENFOAM AND ANSA Adam Kosík Evektor s.r.o., Czech Republic KEYWORDS CFD simulation, mesh generation, OpenFOAM, ANSA ABSTRACT In this paper we describe
Application of CFD Simulation in the Design of a Parabolic Winglet on NACA 2412
, July 2-4, 2014, London, U.K. Application of CFD Simulation in the Design of a Parabolic Winglet on NACA 2412 Arvind Prabhakar, Ayush Ohri Abstract Winglets are angled extensions or vertical projections
Simulation of Fluid-Structure Interactions in Aeronautical Applications
Simulation of Fluid-Structure Interactions in Aeronautical Applications Martin Kuntz Jorge Carregal Ferreira ANSYS Germany D-83624 Otterfing [email protected] December 2003 3 rd FENET Annual Industry
CFD Analysis on Airfoil at High Angles of Attack
CFD Analysis on Airfoil at High Angles of Attack Dr.P.PrabhakaraRao¹ & Sri Sampath.V² Department of Mechanical Engineering,Kakatiya Institute of Technology& Science Warangal-506015 1 [email protected],
Numerical Approach Aspects for the Investigation of the Longitudinal Static Stability of a Transport Aircraft with Circulation Control
Numerical Approach Aspects for the Investigation of the Longitudinal Static Stability of a Transport Aircraft with Circulation Control Dennis Keller Abstract The aim of the investigation is to gain more
High-Lift Systems. High Lift Systems -- Introduction. Flap Geometry. Outline of this Chapter
High-Lift Systems Outline of this Chapter The chapter is divided into four sections. The introduction describes the motivation for high lift systems, and the basic concepts underlying flap and slat systems.
CFD analysis for road vehicles - case study
CFD analysis for road vehicles - case study Dan BARBUT*,1, Eugen Mihai NEGRUS 1 *Corresponding author *,1 POLITEHNICA University of Bucharest, Faculty of Transport, Splaiul Independentei 313, 060042, Bucharest,
ME6130 An introduction to CFD 1-1
ME6130 An introduction to CFD 1-1 What is CFD? Computational fluid dynamics (CFD) is the science of predicting fluid flow, heat and mass transfer, chemical reactions, and related phenomena by solving numerically
Aerodynamic Department Institute of Aviation. Adam Dziubiński CFD group FLUENT
Adam Dziubiński CFD group IoA FLUENT Content Fluent CFD software 1. Short description of main features of Fluent 2. Examples of usage in CESAR Analysis of flow around an airfoil with a flap: VZLU + ILL4xx
Reynolds Averaged Navier-Stokes Analysis for Civil Transport Aircraft using Structured and Unstructured grids
14 th Annual CFD Symposium 10 th 11 th August 2012, Bangalore Reynolds Averaged Navier-Stokes Analysis for Civil Transport Aircraft using Structured and Unstructured grids Vishal S. Shirbhate CTFD Division,
Drag Prediction of Engine Airframe Interference Effects with CFX-5
JOURNAL OF AIRCRAFT Vol. 42, No. 6, November December 2005 Drag Prediction of Engine Airframe Interference Effects with CFX-5 R. B. Langtry, M. Kuntz, and F. R. Menter ANSYS CFX Germany, 83624 Otterfing,
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
University Turbine Systems Research 2012 Fellowship Program Final Report. Prepared for: General Electric Company
University Turbine Systems Research 2012 Fellowship Program Final Report Prepared for: General Electric Company Gas Turbine Aerodynamics Marion Building 300 Garlington Rd Greenville, SC 29615, USA Prepared
Compatibility and Accuracy of Mesh Generation in HyperMesh and CFD Simulation with Acusolve for Torque Converter
Compatibility and Accuracy of Mesh Genen in HyperMesh and CFD Simulation with Acusolve for Converter Kathiresan M CFD Engineer Valeo India Private Limited Block - A, 4th Floor, TECCI Park, No. 176 Rajiv
Customer Training Material. Lecture 2. Introduction to. Methodology ANSYS FLUENT. ANSYS, Inc. Proprietary 2010 ANSYS, Inc. All rights reserved.
Lecture 2 Introduction to CFD Methodology Introduction to ANSYS FLUENT L2-1 What is CFD? Computational Fluid Dynamics (CFD) is the science of predicting fluid flow, heat and mass transfer, chemical reactions,
CFD Simulation of the NREL Phase VI Rotor
CFD Simulation of the NREL Phase VI Rotor Y. Song* and J. B. Perot # *Theoretical & Computational Fluid Dynamics Laboratory, Department of Mechanical & Industrial Engineering, University of Massachusetts
CCTech TM. ICEM-CFD & FLUENT Software Training. Course Brochure. Simulation is The Future
. CCTech TM Simulation is The Future ICEM-CFD & FLUENT Software Training Course Brochure About. CCTech Established in 2006 by alumni of IIT Bombay. Our motive is to establish a knowledge centric organization
Flap Optimization for Take-off and Landing
Proceedings of the 10th Brazilian Congress of Thermal Sciences and Engineering -- ENCIT 2004 Braz. Soc. of Mechanical Sciences and Engineering -- ABCM, Rio de Janeiro, Brazil, Nov. 29 -- Dec. 03, 2004
Multiphase Flow - Appendices
Discovery Laboratory Multiphase Flow - Appendices 1. Creating a Mesh 1.1. What is a geometry? The geometry used in a CFD simulation defines the problem domain and boundaries; it is the area (2D) or volume
Using CFD to improve the design of a circulating water channel
2-7 December 27 Using CFD to improve the design of a circulating water channel M.G. Pullinger and J.E. Sargison School of Engineering University of Tasmania, Hobart, TAS, 71 AUSTRALIA Abstract Computational
AIAA CFD DRAG PREDICTION WORKSHOP: AN OVERVIEW
5 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES AIAA CFD DRAG PREDICTION WORKSHOP: AN OVERVIEW Kelly R. Laflin Cessna Aircraft Company Keywords: AIAA, CFD, DPW, drag, transonic Abstract An overview
CFD ANALYSIS OF RAE 2822 SUPERCRITICAL AIRFOIL AT TRANSONIC MACH SPEEDS
CFD ANALYSIS OF RAE 2822 SUPERCRITICAL AIRFOIL AT TRANSONIC MACH SPEEDS K.Harish Kumar 1, CH.Kiran Kumar 2, T.Naveen Kumar 3 1 M.Tech Thermal Engineering, Sanketika Institute of Technology & Management,
CFD Applications using CFD++ Paul Batten & Vedat Akdag
CFD Applications using CFD++ Paul Batten & Vedat Akdag Metacomp Products available under Altair Partner Program CFD++ Introduction Accurate multi dimensional polynomial framework Robust on wide variety
CONVERGE Features, Capabilities and Applications
CONVERGE Features, Capabilities and Applications CONVERGE CONVERGE The industry leading CFD code for complex geometries with moving boundaries. Start using CONVERGE and never make a CFD mesh again. CONVERGE
CFD Analysis of Supersonic Exhaust Diffuser System for Higher Altitude Simulation
Page1 CFD Analysis of Supersonic Exhaust Diffuser System for Higher Altitude Simulation ABSTRACT Alan Vincent E V P G Scholar, Nehru Institute of Engineering and Technology, Coimbatore Tamil Nadu A high
NACA Nomenclature NACA 2421. NACA Airfoils. Definitions: Airfoil Geometry
0.40 m 0.21 m 0.02 m NACA Airfoils 6-Feb-08 AE 315 Lesson 10: Airfoil nomenclature and properties 1 Definitions: Airfoil Geometry z Mean camber line Chord line x Chord x=0 x=c Leading edge Trailing edge
PARAMETRIC INVESTIGATION OF A HIGH-LIFT AIRFOIL AT HIGH REYNOLDS NUMBERS. John C. Lin* NASA Langley Research Center, Hampton, VA 23681-0001.
PARAMETRIC INVESTIGATION OF A HIGH-LIFT AIRFOIL AT HIGH REYNOLDS NUMBERS John C. Lin* NASA Langley Research Center, Hampton, VA 23681-0001 and Chet J. Dominik McDonnell Douglas Aerospace, Long Beach, CA
Programme Discussions Wissenschaftstag Braunschweig 2015 Laminarität für zukünftige Verkehrsflugzeuge
Programme Discussions Wissenschaftstag Braunschweig 2015 Kevin Nicholls, EIVW Prepared by Heinz Hansen TOP-LDA Leader, ETEA Presented by Bernhard Schlipf, ESCRWG Laminarität für zukünftige Verkehrsflugzeuge
Hydrodynamic Loads on Two-Dimensional Sheets of Netting within the Range of Small Angels of Attack
Hydrodynamic Loads on Two-Dimensional Sheets of Netting within the Range of Small Angels of Attack by Mathias Paschen & Karsten Breddermann 10 th International Workshop Methods for the Development and
Circulation Control NASA activities
National Aeronautics and Space Administration Circulation Control NASA activities Dr. Gregory S. Jones Dr. William E. Millholen II Research Engineers NASA Langley Research Center Active High Lift and Impact
Overset Grids Technology in STAR-CCM+: Methodology and Applications
Overset Grids Technology in STAR-CCM+: Methodology and Applications Eberhard Schreck, Milovan Perić and Deryl Snyder [email protected] [email protected] [email protected]
Fully Automatic Hex Dominant Mesher. Paul Gilfrin Sharc Ltd
Fully Automatic Hex Dominant Mesher Paul Gilfrin Sharc Ltd Sharc Ltd UK About Sharc Developer of Harpoon Founded in 1997 Distributors of Ensight Engineers with CFD/FEA experience Specialise in the integration
AN EFFECT OF GRID QUALITY ON THE RESULTS OF NUMERICAL SIMULATIONS OF THE FLUID FLOW FIELD IN AN AGITATED VESSEL
14 th European Conference on Mixing Warszawa, 10-13 September 2012 AN EFFECT OF GRID QUALITY ON THE RESULTS OF NUMERICAL SIMULATIONS OF THE FLUID FLOW FIELD IN AN AGITATED VESSEL Joanna Karcz, Lukasz Kacperski
NACA 2415- FINDING LIFT COEFFICIENT USING CFD, THEORETICAL AND JAVAFOIL
NACA 2415- FINDING LIFT COEFFICIENT USING CFD, THEORETICAL AND JAVAFOIL Sarfaraj Nawaz Shaha 1, M. Sadiq A. Pachapuri 2 1 P.G. Student, MTech Design Engineering, KLE Dr. M S Sheshgiri College of Engineering
CALIFORNIA STATE UNIVERSITY NORTHRIDGE. Evaluation of Ground Effect on the Drag on an HPV Fairing Using CFD
CALIFORNIA STATE UNIVERSITY NORTHRIDGE Evaluation of Ground Effect on the Drag on an HPV Fairing Using CFD A thesis submitted in partial fulfillment of the requirements For the degree of Master of Science
NUMERICAL ANALYSIS OF WELLS TURBINE FOR WAVE POWER CONVERSION
Engineering Review Vol. 32, Issue 3, 141-146, 2012. 141 NUMERICAL ANALYSIS OF WELLS TURBINE FOR WAVE POWER CONVERSION Z. 1* L. 1 V. 2 M. 1 1 Department of Fluid Mechanics and Computational Engineering,
Express Introductory Training in ANSYS Fluent Lecture 1 Introduction to the CFD Methodology
Express Introductory Training in ANSYS Fluent Lecture 1 Introduction to the CFD Methodology Dimitrios Sofialidis Technical Manager, SimTec Ltd. Mechanical Engineer, PhD PRACE Autumn School 2013 - Industry
Steady Flow: Laminar and Turbulent in an S-Bend
STAR-CCM+ User Guide 6663 Steady Flow: Laminar and Turbulent in an S-Bend This tutorial demonstrates the flow of an incompressible gas through an s-bend of constant diameter (2 cm), for both laminar and
APPENDIX 3-B Airplane Upset Recovery Briefing. Briefing. Figure 3-B.1
APPENDIX 3-B Airplane Upset Recovery Briefing Industry Solutions for Large Swept-Wing Turbofan Airplanes Typically Seating More Than 100 Passengers Briefing Figure 3-B.1 Revision 1_August 2004 Airplane
CFD Lab Department of Engineering The University of Liverpool
Development of a CFD Method for Aerodynamic Analysis of Large Diameter Horizontal Axis wind turbines S. Gomez-Iradi, G.N. Barakos and X. Munduate 2007 joint meeting of IEA Annex 11 and Annex 20 Risø National
GAMBIT Demo Tutorial
GAMBIT Demo Tutorial Wake of a Cylinder. 1.1 Problem Description The problem to be considered is schematically in fig. 1. We consider flow across a cylinder and look at the wake behind the cylinder. Air
Customer Training Material. Lecture 4. Meshing in Mechanical. Mechanical. ANSYS, Inc. Proprietary 2010 ANSYS, Inc. All rights reserved.
Lecture 4 Meshing in Mechanical Introduction to ANSYS Mechanical L4-1 Chapter Overview In this chapter controlling meshing operations is described. Topics: A. Global Meshing Controls B. Local Meshing Controls
HowTo Rhino & ICEM. 1) New file setup: choose Millimeter (automatically converts to Meters if imported to ICEM)
HowTo Rhino & ICEM Simple 2D model 1) New file setup: choose Millimeter (automatically converts to Meters if imported to ICEM) 2) Set units: File Properties Units: Model units: should already be Millimeters
ANSA. www.beta-cae.gr. quality and performance in automatic mesh generation. p i o n e e r i n g software systems
ANSA p i o n e e r i n g software systems quality and performance in automatic mesh generation courtesy of Dr. Ing h.c.f. Porsche AG TM www.beta-cae.gr quality and performance in automatic mesh generation
CFD Simulations and Wind Tunnel Experiments of a Generic Split-Canard Air-to-Air Missile at High Angles of Attack in Turbulent Subsonic Flow
AIAA Atmospheric Flight Mechanics Conference 08-11 August 2011, Portland, Oregon AIAA 2011-6335 CFD Simulations and Wind Tunnel Experiments of a Generic Split-Canard Air-to-Air Missile at High Angles of
ENHANCEMENT OF AERODYNAMIC PERFORMANCE OF A FORMULA-1 RACE CAR USING ADD-ON DEVICES B. N. Devaiah 1, S. Umesh 2
ENHANCEMENT OF AERODYNAMIC PERFORMANCE OF A FORMULA-1 RACE CAR USING ADD-ON DEVICES B. N. Devaiah 1, S. Umesh 2 1- M. Sc. [Engg.] Student, 2- Asst. Professor Automotive and Aeronautical Engineering Department,
Basics of vehicle aerodynamics
Basics of vehicle aerodynamics Prof. Tamás Lajos Budapest University of Technology and Economics Department of Fluid Mechanics University of Rome La Sapienza 2002 Influence of flow characteristics on the
Aeronautical Testing Service, Inc. 18820 59th DR NE Arlington, WA 98223 USA. CFD and Wind Tunnel Testing: Complimentary Methods for Aircraft Design
Aeronautical Testing Service, Inc. 18820 59th DR NE Arlington, WA 98223 USA CFD and Wind Tunnel Testing: Complimentary Methods for Aircraft Design Background Introduction ATS Company Background New and
Comparison between OpenFOAM CFD & BEM theory for variable speed variable pitch HAWT
ITM Web of Conferences 2, 05001 (2014) DOI: 10.1051/itmconf/20140205001 C Owned by the authors, published by EDP Sciences, 2014 Comparison between OpenFOAM CFD & BEM theory for variable speed variable
Numerical Investigation of the Aerodynamic Properties of a Flying Wing Configuration
30th AIAA Applied Aerodynamics Conference 25-28 June 2012, New Orleans, Louisiana AIAA 2012-3325 Numerical Investigation of the Aerodynamic Properties of a Flying Wing Configuration Kerstin C. Huber 1
Simulation at Aeronautics Test Facilities A University Perspective Helen L. Reed, Ph.D., P.E. ASEB meeting, Irvine CA 15 October 2014 1500-1640
Simulation at Aeronautics Test A University Perspective Helen L. Reed, Ph.D., P.E. ASEB meeting, Irvine CA 15 October 2014 1500-1640 Questions How has the ability to do increasingly accurate modeling and
Current Status and Challenges in CFD at the DLR Institute of Aerodynamics and Flow Technology
Current Status and Challenges in CFD at the DLR Institute of Aerodynamics and Flow Technology N. Kroll, C.-C. Rossow DLR, Institute of Aerodynamics and Flow Technology DLR Institute of Aerodynamics and
CFD Analysis of Swept and Leaned Transonic Compressor Rotor
CFD Analysis of Swept and Leaned Transonic Compressor Nivin Francis #1, J. Bruce Ralphin Rose *2 #1 Student, Department of Aeronautical Engineering& Regional Centre of Anna University Tirunelveli India
Computational Aerodynamic Analysis on Store Separation from Aircraft using Pylon
International Journal of Engineering Science Invention (IJESI) ISSN (Online): 2319 6734, ISSN (Print): 2319 6726 www.ijesi.org ǁ PP.27-31 Computational Aerodynamic Analysis on Store Separation from Aircraft
Introduction to ANSYS
Lecture 3 Introduction to ANSYS Meshing 14. 5 Release Introduction to ANSYS Meshing 2012 ANSYS, Inc. March 27, 2014 1 Release 14.5 Introduction to ANSYS Meshing What you will learn from this presentation
Computational Fluid Dynamics
Aerodynamics Computational Fluid Dynamics Industrial Use of High Fidelity Numerical Simulation of Flow about Aircraft Presented by Dr. Klaus Becker / Aerodynamic Strategies Contents Aerodynamic Vision
Computational Modeling of Wind Turbines in OpenFOAM
Computational Modeling of Wind Turbines in OpenFOAM Hamid Rahimi [email protected] ForWind - Center for Wind Energy Research Institute of Physics, University of Oldenburg, Germany Outline Computational
HALE UAV: AeroVironment Pathfinder
HALE UAV: AeroVironment Pathfinder Aerodynamic and Stability Analysis Case Study: Planform Optimization Desta Alemayehu Elizabeth Eaton Imraan Faruque Photo courtesy NASA Dryden Photo Gallery 1 Pathfinder
CRANFIELD UNIVERSITY F MORTEL CRANFIELD TEAM F1: THE FRONT WING SCHOOL OF ENGINEERING CRANFIELD COLLEGE OF AERONAUTICS. MSc THESIS
CRANFIELD UNIVERSITY F MORTEL CRANFIELD TEAM F1: THE FRONT WING SCHOOL OF ENGINEERING CRANFIELD COLLEGE OF AERONAUTICS MSc THESIS CRANFIELD UNIVERSITY SCHOOL OF ENGINEERING CRANFIELD COLLEGE OF AERONAUTICS
Aerodynamic Simulation. Viscous CFD Code Validation
Aerodynamic Simulation using STAR-CCM+ Viscous CFD Code Validation 19 March 2013 CD-adapco STAR-CCM+ Code Validation Efforts Kenneth E. Xiques CRM Solutions 4092 Memorial Pkwy SW, Suite 200 Huntsville,
DESIGN OF THE MODERN FAMILY OF HELICOPTER AIRFOILS 51
DESIGN OF THE MODERN FAMILY OF HELICOPTER AIRFOILS Wojciech KANIA, Wieńczysław STALEWSKI, Bogumiła ZWIERZCHOWSKA Institute of Aviation Summary The paper presents results of numerical design and experimental
Laminar Flow in a Baffled Stirred Mixer
Laminar Flow in a Baffled Stirred Mixer Introduction This exercise exemplifies the use of the rotating machinery feature in the CFD Module. The Rotating Machinery interface allows you to model moving rotating
CFD modelling of floating body response to regular waves
CFD modelling of floating body response to regular waves Dr Yann Delauré School of Mechanical and Manufacturing Engineering Dublin City University Ocean Energy Workshop NUI Maynooth, October 21, 2010 Table
AIR FORCE INSTITUTE OF TECHNOLOGY
CFD Analysis of a T-38 Wing Fence THESIS Daniel Allan Solfelt, Ensign, USN AFIT/GAE/ENY/07-J19 DEPARTMENT OF THE AIR FORCE AIR UNIVERSITY AIR FORCE INSTITUTE OF TECHNOLOGY Wright-Patterson Air Force Base,
CFD Calculations of S809 Aerodynamic Characteristics 1
Walter P. Wolfe Engineering Sciences Center Sandia National Laboratories Albuquerque, NM 87185-0836 Stuart S. Ochs Aerospace Engineering Department Iowa State University Ames, IA 50011 CFD Calculations
CFD Modelling of a Physical Scale Model: assessing model skill. Kristof Verelst 28-11-2014 FHR, Antwerp
CFD Modelling of a Physical Scale Model: assessing model skill Kristof Verelst 28-11-2014 FHR, Antwerp Introduction Introduction WL_13_61 CFD simulations of hydrodynamics for hydraulic structures (00_085)
A NUMERICAL METHOD TO PREDICT THE LIFT OF AIRCRAFT WINGS AT STALL CONDITIONS
Braz. Soc. of Mechanical Sciences and Engineering -- ABCM, Rio de Janeiro, Brazil, Nov. 29 -- Dec. 3, 24 A NUMERICAL METHOD TO PREDICT THE LIFT OF AIRCRAFT WINGS AT STALL CONDITIONS Marcos A. Ortega ITA
Using CEASIOM-SUMO RapidMeshing in Computational Study of. Asymmetric Aircraft Design
Using CEASIOM-SUMO RapidMeshing in Computational Study of Asymmetric Aircraft Design Mengmeng Zhang, Arthur Rizzi Royal Institute of Technology (KTH), Stockholm, Sweden & D. Raymer Conceptual Research
Lift and Drag on an Airfoil ME 123: Mechanical Engineering Laboratory II: Fluids
Lift and Drag on an Airfoil ME 123: Mechanical Engineering Laboratory II: Fluids Dr. J. M. Meyers Dr. D. G. Fletcher Dr. Y. Dubief 1. Introduction In this lab the characteristics of airfoil lift, drag,
Module 6 Case Studies
Module 6 Case Studies 1 Lecture 6.1 A CFD Code for Turbomachinery Flows 2 Development of a CFD Code The lecture material in the previous Modules help the student to understand the domain knowledge required
Wing Design: Major Decisions. Wing Area / Wing Loading Span / Aspect Ratio Planform Shape Airfoils Flaps and Other High Lift Devices Twist
Wing Design: Major Decisions Wing Area / Wing Loading Span / Aspect Ratio Planform Shape Airfoils Flaps and Other High Lift Devices Twist Wing Design Parameters First Level Span Area Thickness Detail Design
Introduction to ANSYS ICEM CFD
Lecture 6 Mesh Preparation Before Output to Solver 14. 0 Release Introduction to ANSYS ICEM CFD 1 2011 ANSYS, Inc. March 22, 2015 Mesh Preparation Before Output to Solver What will you learn from this
Introduction to CFD Analysis
Introduction to CFD Analysis 2-1 What is CFD? Computational Fluid Dynamics (CFD) is the science of predicting fluid flow, heat and mass transfer, chemical reactions, and related phenomena by solving numerically
Introduction to CFD Analysis
Introduction to CFD Analysis Introductory FLUENT Training 2006 ANSYS, Inc. All rights reserved. 2006 ANSYS, Inc. All rights reserved. 2-2 What is CFD? Computational fluid dynamics (CFD) is the science
CFD Analysis of PACE Formula-1 Car
1 CFD Analysis of PACE Formula-1 Car Satyan Chandra 1, Allison Lee 2, Steven Gorrell 3 and C. Greg Jensen 4 1 Brigham Young University, [email protected] 2 Brigham Young University, [email protected]
The Influence of Aerodynamics on the Design of High-Performance Road Vehicles
The Influence of Aerodynamics on the Design of High-Performance Road Vehicles Guido Buresti Department of Aerospace Engineering University of Pisa (Italy) 1 CONTENTS ELEMENTS OF AERODYNAMICS AERODYNAMICS
Modeling wind flow using O.F. Wind, an OpenFOAM based CFD tool: validation of Turbulence Intensity in a testing Suzlon Energy site Ltd.
Modeling wind flow using O.F. Wind, an OpenFOAM based CFD tool: validation of Turbulence Intensity in a testing Suzlon Energy site Ltd. L.Casella 1, W.Langreder 1, A.Fischer 2, M.Ehlen 2, D.Skoutelakos
f o r d e m a n d i n g C F D pre- & post-processing ANSA μετα p i o n e e r i n g software systems www.beta-cae.gr
ANSA μετα p i o n e e r i n g software systems f o r d e m a n d i n g C F D pre- & post-processing TM www.beta-cae.gr ANSA with its powerful functionality provides high efficiency solutions for CFD applications.
Formula 1 Aerodynamic Assessment by Means of CFD Modelling
Formula 1 Aerodynamic Assessment by Means of CFD Modelling DANSIS Automotive Fluid Dynamics Seminar 25 March 2015 Copenhagen Denmark Dr. Lesmana Djayapertapa Senior CFD Consultant LR Senergy Aberdeen -
The UberCloud Experiment
The UberCloud Experiment Technical Computing in the Cloud Case Studies 159, 160, 165, and 166: Computational Fluid Dynamics with ANSYS, CD-adapco, and OpenFOAM Containers in the UberCloud http://www.theubercloud.com
NUMERICAL AND EXPERIMENTAL ANALYSIS OF THE WIND FORCES ACTING ON LNG CARRIER
V European Conference on Computational Fluid Dynamics ECCOMAS CFD 1 J. C. F. Pereira and A. Sequeira (Eds) Lisbon, Portugal, 14 17 June 1 NUMERICAL AND EXPERIMENTAL ANALYSIS OF THE WIND FORCES ACTING ON
STCE. Outline. Introduction. Applications. Ongoing work. Summary. STCE RWTH-Aachen, Industrial Applications of discrete adjoint OpenFOAM, EuroAD 2014
Industrial Applications of discrete adjoint OpenFOAM Arindam Sen Software and Tools for Computational Engineering Science RWTH Aachen University EuroAD 2014, Nice, 16-17. June 2014 Outline Introduction
SBi 2013:12. Use of perforated acoustic panels as supply air diffusers in diffuse ceiling ventilation systems
SBi 2013:12 Use of perforated acoustic panels as supply air diffusers in diffuse ceiling ventilation systems Use of perforated acoustic panels as supply air diffusers in diffuse ceiling ventilation systems
CFD results for TU-154M in landing configuration for an asymmetrical loss in wing length.
length. PAGE [1] CFD results for TU-154M in landing configuration for an asymmetrical loss in wing length. Summary: In CFD work produced by G. Kowaleczko (GK) and sent to the author of this report in 2013
Customer Training Material. Shell Meshing Stamped Part ICEM CFD. ANSYS, Inc. Proprietary 2010 ANSYS, Inc. All rights reserved. WS3.
Workshop 3.1 Shell Meshing Stamped Part Introduction to ANSYS ICEM CFD WS3.1-1 Create Project / Open Geometry File > New Project Enter the Stamping folder Type Stamped-mesh Save File > Geometry > Open
An Overview of the Finite Element Analysis
CHAPTER 1 An Overview of the Finite Element Analysis 1.1 Introduction Finite element analysis (FEA) involves solution of engineering problems using computers. Engineering structures that have complex geometry
Lecture 7 - Meshing. Applied Computational Fluid Dynamics
Lecture 7 - Meshing Applied Computational Fluid Dynamics Instructor: André Bakker http://www.bakker.org André Bakker (2002-2006) Fluent Inc. (2002) 1 Outline Why is a grid needed? Element types. Grid types.
ANSA. www.beta-cae.gr. ANSA for demanding CFD pre-processing. for demanding CFD pre-processing. Model setup. software systems. Morphing & optimization
Model setup - Specification of boundary condition types for ANSYS FLUENT, Star CD/CCM+ and UH-3D. - Complete solution setup for OpenFOAM cases, including initial and boundary condition specification, physical
Validations Of Openfoam Steady State Compressible Solver Rhosimplefoam
Validations Of Openfoam Steady State Compressible Solver Rhosimplefoam Umran Abdul Rahman, and Faizal Mustapha Abstract OpenFOAM steady state solver rhosimplefoam was tested. Reynolds Average Navier Stokes
Prediction of airfoil performance at high Reynolds numbers
Downloaded from orbit.dtu.dk on: Jul 01, 2016 Prediction of airfoil performance at high Reynolds numbers. Sørensen, Niels N.; Zahle, Frederik; Michelsen, Jess Publication date: 2014 Document Version Publisher's
Aeroelastic Investigation of the Sandia 100m Blade Using Computational Fluid Dynamics
Aeroelastic Investigation of the Sandia 100m Blade Using Computational Fluid Dynamics David Corson Altair Engineering, Inc. Todd Griffith Sandia National Laboratories Tom Ashwill (Retired) Sandia National
Very special thanks to Wolfgang Gentzsch and Burak Yenier for making the UberCloud HPC Experiment possible.
Digital manufacturing technology and convenient access to High Performance Computing (HPC) in industry R&D are essential to increase the quality of our products and the competitiveness of our companies.