ITU/FAA Faculty of Aeronautics and Astronautics

Size: px
Start display at page:

Download "ITU/FAA Faculty of Aeronautics and Astronautics"

Transcription

1 S. Banu YILMAZ, Mehmet SAHIN, M. Fevzi UNAL, Istanbul Technical University, 34469, Maslak/Istanbul, TURKEY 65th Annual Meeting of the APS Division of Fluid Dynamics November 18-20, 2012, San Diego, CA

2 Contents ITU/FAA 1. The Motivation 2. Governing Equations and Numerical Formulation 3. Validation Cases Case 1, Re = Case 2, Re = Simulation Results Tandem Configurations Biplane Configurations 5. Conclusions and Future Work DFD

3 The Motivation ITU/FAA Understanding the Nature 3D, combined pitch plunge sweep motions of birds, insects and fishes Imitating Nature MAVs; potential civil and military applications such as terrestrial and indoor monitoring Alternative propulsion systems Power generators, energy harvesting DFD

4 Governing Equations and Numerical Formulation (continued ) The governing equations of an incompressible unsteady Newtonian fluid can be written in dimensionless form as follows: Integrating the differential equations over an arbitrary moving irregular control volume. DFD

5 Governing Equations and Numerical Formulation (continued ) An unstructured finite volume solver based on Arbitrary Lagrangian-Eulerian formulation is utilized in order to solve the incompressible unsteady Navier-Stokes equations. (a) Two-dimensional dual volume (b) Three-dimensional dual volume The side centered finite volume method used by Hwang (1995) and Rida et al. (1997). The present arrangement of the primitive variables leads to a stable numerical scheme and it does not require any ad-hoc modifications in order to enhance pressure-velocity coupling. The most appealing feature of this primitive variable arrangement is the availability of very efficient multigrid solvers. DFD

6 Governing Equations and Numerical Formulation (continued ) The discrete contribution from the right cell is given for the momentum equation along the x-axis. The time derivation: The convective term The pressure term The viscous term DFD

7 Governing Equations and Numerical Formulation (continued ) The continuity equation is integrated within each quadrilateral elements and evaluated using the mid-point rule on each of the element faces. The discretization of above equations leads to a saddle point problem of the form: The preconditioner matrix is Where. For the inverse of the scaled Laplacian S, we use twocycle AMG solver provided by the HYPRE library, a high performance preconditioning package developed at Lawrence Livermore National Laboratory, which we access through the PETSC library. DFD

8 Computational Domain ITU/FAA The computational mesh consists of 747,597 quadrilateral elements and 748,508 nodes (DOF = 3,739,807) including a fine boundary layer region around airfoil. The boundary layer grid is created using Gambit2.1.6 software and the rest of the grid is generated via Cubit9.1 software using mapping and paving algorithms. DFD

9 Validation- C a s e 1 Re=20000, k=4, h= (Lai and Platzer, AIAA Journal, 1999) (Young and Lai, Aust. Fluid Mech. Conf., 2001) Current study Current study DFD

10 Validation- C a s e 2 Re=252, k=12.3, h=0.12 (Jones and Platzer, Exp. Fluids, 2009) Current study DFD

11 Grid Convergence Coarse mesh ( elements) Fine mesh ( elements) DFD

12 Effect of Phase Angle Deflected = 180 o Depending on the location of start-up vortices, the calculations indicate strong hysteresis effects and multiple periodic solutions. Symmetric = 90 o DFD

13 3D Solution NACA0012 Re = 252 = 180 y t = 0.12 sin (12.3t + ) 0 < z < c No strong three-dimensional effects are visible. Mild three-dimensional effects 2,040,568 elements DOF= 20,598,994 DFD

14 Numerical Simulations ITU/FAA Biplane Asynchroneous, closer Detailed look DFD

15 Flow Parameters ITU/FAA The Reynolds number is chosen as 252 The reduced frequency k is 12.3 and plunge amplitude h is 0.12 The equation of motion is, The time between two iterations t is calculated as 1/400 of a period of airfoil motion as, k = 2πfc/U y t = 0.12 sin (12.3t + ) t = 2π/(400f) DFD

16 Flow Parameters (continued ) ITU/FAA y = h sin( t) k = 12.3 h = 0.12 kh = 1.48 (Tuncer and Platzer, AIAA Jou., 1996) DFD

17 Simulation Results DFD

18 Tandem Wing Configurations ITU/FAA Tandem Shifted Tandem, -0.12c Tandem Synchroneous Tandem Asynchroneous DFD

19 Biplane Wing Configurations ITU/FAA Biplane Biplane Synchroneous Biplane Aynchroneous Biplane Asynchroneous-closer DFD

20 Comparison of Tandem Configurations A period of shedding Tandem Shifted Tandem Tandem Synchroneous Tandem Asynchroneous DFD

21 Comparison of Tandem Configurations Streamlines Tandem Shifted Tandem Single Tandem Synchroneous Tandem Asynchroneous DFD

22 Comparison of Biplane Configurations A period of shedding Biplane Biplane Synchroneous later on Biplane Aynchroneous Biplane Asynchroneous-closer DFD

23 Comparison of Biplane Configurations Streamlines Biplane Biplane Synchroneous Single Biplane Aynchroneous Biplane Asynchroneous-closer DFD

24 C T & Power Spectrum - Tandem Configurations Single Tandem Forewing ITU/FAA Hindwing C T mean = C T mean = C T mean = Shifted Tandem C T mean = C T mean = DFD

25 C T & Power Spectrum - Tandem Configurations Single Tandem Synchroneous ITU/FAA Forewing Hindwing C T = mean C T = mean C T = mean Tandem Asynchroneous C T mean = C T mean = DFD

26 C T & Power Spectrum - Biplane Configurations Single Biplane Upper wing ITU/FAA Lower wing C T mean = C T mean = C T mean = Biplane Synchroneous C T mean = C T mean = DFD

27 C T & Power Spectrum - Biplane Configurations Single Biplane Asynchroneous Upper wing ITU/FAA Lower wing C T mean = C T mean = C T mean = Biplane Asynchroneous closer C T mean = C T mean = DFD

28 Mean Lift and Thrust DFD

29 Experimental Setup Large scale water channel Kollmorgen/Danaher Motion AKM33E servo motor and gear system U DFD

30 Conclusions and Future Work ITU/FAA The numerical method has been validated for the numerical and the experimental results available in the literature. The temporal and spatial resolution scales have been investigated. The single plunging airfoil case at Re=252 reveals a very strong hysteresis effects and multiple periodic solutions even though the Reynolds number is relatively low. Several wing combinations are investigated, by means of flow field characteristics and force statistics, The most interesting vortex fields appeared at biplane synchroneous and asynchroneous cases, In tandem synchroneus, biplane asynchroneous and asynchroneous-closer cases, the thrust force is increased considerably. Frequency, Reynolds number effects will be studied both experimentally and numerically. Experiments will be conducted using PIV (Particle Image Velocimetry) for further validation of the results. DFD

31 Acknowledgement ITU/FAA The authors gratefully acknowledge the use of the Chimera machine at the at ITU, the computing resources provided by the National Center for High Performance Computing of Turkey (UYBHM) under grant number and the computing facilities at TUBITAK ULAKBIM, High Performance and Grid Computing Center. DFD

32 Thank you, Any questions? DFD

33 Mesh Refinement 1 st order, coarse mesh ( elements) 2 nd order converged solution Although fine mesh and coarse mesh solutions coincide Mesh convergency is not enough for first order time discretization. 1 st order, fine mesh ( elements) DFD

34 Time Independency 1 st order, t 2 nd order converged solution 1 st order time discretization converges slowly. So, as t takes smaller values solution is converged. 1 st order, t/4 DFD

CFD Analysis of 2-D Unsteady Flow Past a Square Cylinder at an Angle of Incidence

CFD Analysis of 2-D Unsteady Flow Past a Square Cylinder at an Angle of Incidence CFD Analysis of 2-D Unsteady Flow Past a Square Cylinder at an Angle of Incidence Kavya H.P, Banjara Kotresha 2, Kishan Naik 3 Dept. of Studies in Mechanical Engineering, University BDT College of Engineering,

More information

An Embedded Boundary Method with Adaptive Mesh Refinements

An Embedded Boundary Method with Adaptive Mesh Refinements An Embedded Boundary Method with Adaptive Mesh Refinements Marcos Vanella and Elias Balaras 8 th World Congress on Computational Mechanics, WCCM8 5 th European Congress on Computational Methods in Applied

More information

Driven Cavity Example

Driven Cavity Example BMAppendixI.qxd 11/14/12 6:55 PM Page I-1 I CFD Driven Cavity Example I.1 Problem One of the classic benchmarks in CFD is the driven cavity problem. Consider steady, incompressible, viscous flow in a square

More information

High-Lift Aerodynamics: STAR-CCM+ Applied to AIAA HiLiftWS1 D. Snyder

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

More information

Three-dimensional numerical simulations of flapping wings at low Reynolds numbers

Three-dimensional numerical simulations of flapping wings at low Reynolds numbers Three-dimensional numerical simulations of flapping wings at low Reynolds numbers OpenFOAM Workshop, Zagreb Frank Bos, Bas van Oudheusden, Hester Bijl 7-9 June 2007 1/22 Delft University of Technology

More information

Verification and Validation of Turbulent Flow around a Clark-Y Airfoil

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

More information

ALE Seamless Immersed Boundary Method with Overset Grid System for Multiple Moving Objects

ALE Seamless Immersed Boundary Method with Overset Grid System for Multiple Moving Objects Tenth International Conference on Computational Fluid Dynamics (ICCFD10), Barcelona,Spain, July 9-13, 2018 ICCFD10-047 ALE Seamless Immersed Boundary Method with Overset Grid System for Multiple Moving

More information

Keywords: CFD, aerofoil, URANS modeling, flapping, reciprocating movement

Keywords: CFD, aerofoil, URANS modeling, flapping, reciprocating movement L.I. Garipova *, A.N. Kusyumov *, G. Barakos ** * Kazan National Research Technical University n.a. A.N.Tupolev, ** School of Engineering - The University of Liverpool Keywords: CFD, aerofoil, URANS modeling,

More information

Investigation of cross flow over a circular cylinder at low Re using the Immersed Boundary Method (IBM)

Investigation of cross flow over a circular cylinder at low Re using the Immersed Boundary Method (IBM) Computational Methods and Experimental Measurements XVII 235 Investigation of cross flow over a circular cylinder at low Re using the Immersed Boundary Method (IBM) K. Rehman Department of Mechanical Engineering,

More information

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 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

More information

Computational Study of Unsteady Flows around Dragonfly and Smooth Airfoils at Low Reynolds Numbers

Computational Study of Unsteady Flows around Dragonfly and Smooth Airfoils at Low Reynolds Numbers 46th AIAA Aerospace Sciences Meeting and Exhibit 7 - January 8, Reno, Nevada AIAA 8-85 Computational Study of Unsteady Flows around Dragonfly and Smooth Airfoils at Low Reynolds Numbers H. Gao, Hui Hu,

More information

Numerical studies for Flow Around a Sphere regarding different flow regimes caused by various Reynolds numbers

Numerical studies for Flow Around a Sphere regarding different flow regimes caused by various Reynolds numbers Numerical studies for Flow Around a Sphere regarding different flow regimes caused by various Reynolds numbers R. Jendrny, H. Damanik, O. Mierka, S. Turek Institute of Applied Mathematics (LS III), TU

More information

1.2 Numerical Solutions of Flow Problems

1.2 Numerical Solutions of Flow Problems 1.2 Numerical Solutions of Flow Problems DIFFERENTIAL EQUATIONS OF MOTION FOR A SIMPLIFIED FLOW PROBLEM Continuity equation for incompressible flow: 0 Momentum (Navier-Stokes) equations for a Newtonian

More information

Computational Study of Laminar Flowfield around a Square Cylinder using Ansys Fluent

Computational Study of Laminar Flowfield around a Square Cylinder using Ansys Fluent MEGR 7090-003, Computational Fluid Dynamics :1 7 Spring 2015 Computational Study of Laminar Flowfield around a Square Cylinder using Ansys Fluent Rahul R Upadhyay Master of Science, Dept of Mechanical

More information

NUMERICAL SIMULATION OF 3D FLAPPING WING BASED ON CHIMERA METHOD

NUMERICAL SIMULATION OF 3D FLAPPING WING BASED ON CHIMERA METHOD 26 TH INTERNATIONAL CONGRESS OF THE AERONAUTICAL SCIENCES NUMERICAL SIMULATION OF 3D FLAPPING WING Wenqing Yang, Bifeng Song, Wenping Song School of Aeronautics, Northwestern Polytechnical University,

More information

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 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

More information

Coupling of STAR-CCM+ to Other Theoretical or Numerical Solutions. Milovan Perić

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

More information

Strömningslära Fluid Dynamics. Computer laboratories using COMSOL v4.4

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

More information

The Development of a Navier-Stokes Flow Solver with Preconditioning Method on Unstructured Grids

The Development of a Navier-Stokes Flow Solver with Preconditioning Method on Unstructured Grids Proceedings of the International MultiConference of Engineers and Computer Scientists 213 Vol II, IMECS 213, March 13-15, 213, Hong Kong The Development of a Navier-Stokes Flow Solver with Preconditioning

More information

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 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

More information

Introduction to ANSYS CFX

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

More information

Optimization of the Flapping Wing Systems for a Micro Air Vehicle

Optimization of the Flapping Wing Systems for a Micro Air Vehicle Final Report Title: Optimization of the Flapping Wing Systems for a Micro Air Vehicle AFOSR/AOARD Reference Number: AOARD-09-4103 AFOSR/AOARD Program Manager: John Seo Period of Performance: June 2009

More information

A higher-order finite volume method with collocated grid arrangement for incompressible flows

A higher-order finite volume method with collocated grid arrangement for incompressible flows Computational Methods and Experimental Measurements XVII 109 A higher-order finite volume method with collocated grid arrangement for incompressible flows L. Ramirez 1, X. Nogueira 1, S. Khelladi 2, J.

More information

Simulation of the Dynamics of Micro Air Vehicles. Ravi Ramamurti and William Sandberg

Simulation of the Dynamics of Micro Air Vehicles. Ravi Ramamurti and William Sandberg AIAA 2000-0896 Simulation of the Dynamics of Micro Air Vehicles Ravi Ramamurti and William Sandberg Laboratory for Computational Physics and Fluid Dynamics Naval Research Laboratory Washington, D.C. 20375

More information

MESHLESS SOLUTION OF INCOMPRESSIBLE FLOW OVER BACKWARD-FACING STEP

MESHLESS SOLUTION OF INCOMPRESSIBLE FLOW OVER BACKWARD-FACING STEP Vol. 12, Issue 1/2016, 63-68 DOI: 10.1515/cee-2016-0009 MESHLESS SOLUTION OF INCOMPRESSIBLE FLOW OVER BACKWARD-FACING STEP Juraj MUŽÍK 1,* 1 Department of Geotechnics, Faculty of Civil Engineering, University

More information

Modelling the Unsteady Loads of Plunging Airfoils in Attached, Light and Deep Stall Conditions

Modelling the Unsteady Loads of Plunging Airfoils in Attached, Light and Deep Stall Conditions Modelling the Unsteady Loads of Plunging Airfoils in Attached, Light and Deep Stall Conditions N. Chiereghin, D.J.Cleaver, I. Gursul, S.Bull DiPart 2017 Partnership with Contents Introduction Aims and

More information

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 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)

More information

Verification of Moving Mesh Discretizations

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

More information

Development of an Integrated Computational Simulation Method for Fluid Driven Structure Movement and Acoustics

Development of an Integrated Computational Simulation Method for Fluid Driven Structure Movement and Acoustics Development of an Integrated Computational Simulation Method for Fluid Driven Structure Movement and Acoustics I. Pantle Fachgebiet Strömungsmaschinen Karlsruher Institut für Technologie KIT Motivation

More information

High-order mesh generation for CFD solvers

High-order mesh generation for CFD solvers High-order mesh generation for CFD solvers M. Turner, D. Moxey, S. Sherwin, J. Peiró Department of Aeronautics, Imperial College London DiPaRT 2015 Annual Meeting, Bristol, UK 17 th November 2015 Overview

More information

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 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

More information

Possibility of Implicit LES for Two-Dimensional Incompressible Lid-Driven Cavity Flow Based on COMSOL Multiphysics

Possibility of Implicit LES for Two-Dimensional Incompressible Lid-Driven Cavity Flow Based on COMSOL Multiphysics Possibility of Implicit LES for Two-Dimensional Incompressible Lid-Driven Cavity Flow Based on COMSOL Multiphysics Masanori Hashiguchi 1 1 Keisoku Engineering System Co., Ltd. 1-9-5 Uchikanda, Chiyoda-ku,

More information

A Scalable GPU-Based Compressible Fluid Flow Solver for Unstructured Grids

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

More information

Analysis of Flow Dynamics of an Incompressible Viscous Fluid in a Channel

Analysis of Flow Dynamics of an Incompressible Viscous Fluid in a Channel Analysis of Flow Dynamics of an Incompressible Viscous Fluid in a Channel Deepak Kumar Assistant Professor, Department of Mechanical Engineering, Amity University Gurgaon, India E-mail: deepak209476@gmail.com

More information

Numerical Simulation Study on Aerodynamic Characteristics of the High Speed Train under Crosswind

Numerical Simulation Study on Aerodynamic Characteristics of the High Speed Train under Crosswind 2017 2nd International Conference on Industrial Aerodynamics (ICIA 2017) ISBN: 978-1-60595-481-3 Numerical Simulation Study on Aerodynamic Characteristics of the High Speed Train under Crosswind Fan Zhao,

More information

NUMERICAL 3D TRANSONIC FLOW SIMULATION OVER A WING

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)

More information

CFD VALIDATION FOR SURFACE COMBATANT 5415 STRAIGHT AHEAD AND STATIC DRIFT 20 DEGREE CONDITIONS USING STAR CCM+

CFD VALIDATION FOR SURFACE COMBATANT 5415 STRAIGHT AHEAD AND STATIC DRIFT 20 DEGREE CONDITIONS USING STAR CCM+ CFD VALIDATION FOR SURFACE COMBATANT 5415 STRAIGHT AHEAD AND STATIC DRIFT 20 DEGREE CONDITIONS USING STAR CCM+ by G. J. Grigoropoulos and I..S. Kefallinou 1. Introduction and setup 1. 1 Introduction The

More information

A MESH ADAPTATION METHOD FOR SIMULATION OF UNSTEADY FLOWS

A MESH ADAPTATION METHOD FOR SIMULATION OF UNSTEADY FLOWS A MESH ADAPTATION METHOD FOR SIMULATION OF UNSTEAD FLOWS C. H. Zhou* * Department of Aerodynamics, Nanjing University of Aeronautics and Astronautics, Nanjing, 6, China Keywords: mesh adaptation, unsteady

More information

A THREE-DIMENSIONAL FLAPPING WING MECHANISM FOR WIND TUNNEL EXPERIMENTS

A THREE-DIMENSIONAL FLAPPING WING MECHANISM FOR WIND TUNNEL EXPERIMENTS A THREE-DIMENSIONAL FLAPPING WING MECHANISM FOR WIND TUNNEL EXPERIMENTS Boyang Li, Bifeng Song, Liguang Wang School of Aeronautics, Northwestern Polytechnical University, Xi an, P.R. China, 710072 Keywords:

More information

A COUPLED FINITE VOLUME SOLVER FOR THE SOLUTION OF LAMINAR TURBULENT INCOMPRESSIBLE AND COMPRESSIBLE FLOWS

A COUPLED FINITE VOLUME SOLVER FOR THE SOLUTION OF LAMINAR TURBULENT INCOMPRESSIBLE AND COMPRESSIBLE FLOWS A COUPLED FINITE VOLUME SOLVER FOR THE SOLUTION OF LAMINAR TURBULENT INCOMPRESSIBLE AND COMPRESSIBLE FLOWS L. Mangani Maschinentechnik CC Fluidmechanik und Hydromaschinen Hochschule Luzern Technik& Architektur

More information

DNV GL s 16th Technology Week

DNV GL s 16th Technology Week OIL & GAS DNV GL s 16th Technology Week Advanced Simulation for Offshore Application: Application of CFD for Computing VIM of Floating Structures 1 SAFER, SMARTER, GREENER OUTLINE Introduction Elements

More information

Experimental Studies of Flapping-wing Aerodynamics

Experimental Studies of Flapping-wing Aerodynamics Experimental Studies of Flapping-wing Aerodynamics N. Phillips Aeromechanical Systems Group Cranfield University Defence Academy of the UK Shrivenham, Swindon, UK SN6 8LA Tel: 01793 78 5271 Fax: 01793

More information

cuibm A GPU Accelerated Immersed Boundary Method

cuibm A GPU Accelerated Immersed Boundary Method cuibm A GPU Accelerated Immersed Boundary Method S. K. Layton, A. Krishnan and L. A. Barba Corresponding author: labarba@bu.edu Department of Mechanical Engineering, Boston University, Boston, MA, 225,

More information

NUMERICAL SIMULATION OF THE UNSTEADY AERODYNAMICS OF FLAPPING FLIGHT

NUMERICAL SIMULATION OF THE UNSTEADY AERODYNAMICS OF FLAPPING FLIGHT Department of Civil, Environmental and Architectural Engineering University of Genoa NUMERICAL SIMULATION OF THE UNSTEADY AERODYNAMICS OF FLAPPING FLIGHT Joel GUERRERO A thesis submitted for the degree

More information

Application of Hydrodynamics and Dynamics Models for Efficient Operation of Modular Mini-AUVs in Shallow and Very-Shallow Waters

Application of Hydrodynamics and Dynamics Models for Efficient Operation of Modular Mini-AUVs in Shallow and Very-Shallow Waters Application of Hydrodynamics and Dynamics Models for Efficient Operation of Modular Mini-AUVs in Shallow and Very-Shallow Waters P. Ananthakrishnan Department of Ocean Engineering Florida Atlantic University

More information

Solution Recording and Playback: Vortex Shedding

Solution Recording and Playback: Vortex Shedding STAR-CCM+ User Guide 6663 Solution Recording and Playback: Vortex Shedding This tutorial demonstrates how to use the solution recording and playback module for capturing the results of transient phenomena.

More information

Designing flapping wings as oscillating structures

Designing flapping wings as oscillating structures th World Congress on Structural and Multidisciplinary Optimization May 9-4,, Orlando, Florida, USA Designing flapping wings as oscillating structures Zhiyuan Zhang, Ashok V. Kumar, Raphael T. Haftka University

More information

2.7 Cloth Animation. Jacobs University Visualization and Computer Graphics Lab : Advanced Graphics - Chapter 2 123

2.7 Cloth Animation. Jacobs University Visualization and Computer Graphics Lab : Advanced Graphics - Chapter 2 123 2.7 Cloth Animation 320491: Advanced Graphics - Chapter 2 123 Example: Cloth draping Image Michael Kass 320491: Advanced Graphics - Chapter 2 124 Cloth using mass-spring model Network of masses and springs

More information

The viscous forces on the cylinder are proportional to the gradient of the velocity field at the

The viscous forces on the cylinder are proportional to the gradient of the velocity field at the Fluid Dynamics Models : Flow Past a Cylinder Flow Past a Cylinder Introduction The flow of fluid behind a blunt body such as an automobile is difficult to compute due to the unsteady flows. The wake behind

More information

Direct numerical simulations of flow and heat transfer over a circular cylinder at Re = 2000

Direct numerical simulations of flow and heat transfer over a circular cylinder at Re = 2000 Journal of Physics: Conference Series PAPER OPEN ACCESS Direct numerical simulations of flow and heat transfer over a circular cylinder at Re = 2000 To cite this article: M C Vidya et al 2016 J. Phys.:

More information

Effects of pitching rotation on aerodynamics of tandem flapping wing sections of a hovering dragonfly

Effects of pitching rotation on aerodynamics of tandem flapping wing sections of a hovering dragonfly THE AERONAUTICAL JOURNAL NOVEMBER 2010 VOL 114 NO 1161 699 Effects of pitching rotation on aerodynamics of tandem flapping wing sections of a hovering dragonfly E. M. Elarbi N. Qin n.qin@sheffield.ac.uk

More information

FEMLAB Exercise 1 for ChE366

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

More information

Viscous/Potential Flow Coupling Study for Podded Propulsors

Viscous/Potential Flow Coupling Study for Podded Propulsors First International Symposium on Marine Propulsors smp 09, Trondheim, Norway, June 2009 Viscous/Potential Flow Coupling Study for Podded Propulsors Eren ÖZSU 1, Ali Can TAKİNACI 2, A.Yücel ODABAŞI 3 1

More information

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 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

More information

Numerical Simulation of Coupled Fluid-Solid Systems by Fictitious Boundary and Grid Deformation Methods

Numerical Simulation of Coupled Fluid-Solid Systems by Fictitious Boundary and Grid Deformation Methods Numerical Simulation of Coupled Fluid-Solid Systems by Fictitious Boundary and Grid Deformation Methods Decheng Wan 1 and Stefan Turek 2 Institute of Applied Mathematics LS III, University of Dortmund,

More information

FOURTH ORDER COMPACT FORMULATION OF STEADY NAVIER-STOKES EQUATIONS ON NON-UNIFORM GRIDS

FOURTH ORDER COMPACT FORMULATION OF STEADY NAVIER-STOKES EQUATIONS ON NON-UNIFORM GRIDS International Journal of Mechanical Engineering and Technology (IJMET Volume 9 Issue 10 October 2018 pp. 179 189 Article ID: IJMET_09_10_11 Available online at http://www.iaeme.com/ijmet/issues.asp?jtypeijmet&vtype9&itype10

More information

Stream Function-Vorticity CFD Solver MAE 6263

Stream Function-Vorticity CFD Solver MAE 6263 Stream Function-Vorticity CFD Solver MAE 66 Charles O Neill April, 00 Abstract A finite difference CFD solver was developed for transient, two-dimensional Cartesian viscous flows. Flow parameters are solved

More information

Profile Catalogue for Airfoil Sections Based on 3D Computations

Profile Catalogue for Airfoil Sections Based on 3D Computations Risø-R-58(EN) Profile Catalogue for Airfoil Sections Based on 3D Computations Franck Bertagnolio, Niels N. Sørensen and Jeppe Johansen Risø National Laboratory Roskilde Denmark December 26 Author: Franck

More information

Advances in Simulation for Marine And Offshore Applications. Milovan Perić

Advances in Simulation for Marine And Offshore Applications. Milovan Perić Advances in Simulation for Marine And Offshore Applications Milovan Perić Introduction Extensions and enhancements in STAR-CCM+ for marine and offshore applications: Creation of irregular long-crested

More information

LARGE EDDY SIMULATION OF VORTEX SHEDDING WITH TRIANGULAR CYLINDER AHEAD OF A SQUARE CYLINDER

LARGE EDDY SIMULATION OF VORTEX SHEDDING WITH TRIANGULAR CYLINDER AHEAD OF A SQUARE CYLINDER The Eighth Asia-Pacific Conference on Wind Engineering, December 10 14, 2013, Chennai, India LARGE EDDY SIMULATION OF VORTEX SHEDDING WITH TRIANGULAR CYLINDER AHEAD OF A SQUARE CYLINDER Akshoy Ranjan Paul

More information

Evaluation of Flow Solver Accuracy using Five Simple Unsteady Validation Cases

Evaluation of Flow Solver Accuracy using Five Simple Unsteady Validation Cases Evaluation of Flow Solver Accuracy using Five Simple Unsteady Validation Cases Bradford E. Green, Ryan Czerwiec Naval Air Systems Command, Patuxent River, MD, 20670 Chris Cureton, Chad Lillian, Sergey

More information

Modeling External Compressible Flow

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

More information

Parallel High-Order Geometric Multigrid Methods on Adaptive Meshes for Highly Heterogeneous Nonlinear Stokes Flow Simulations of Earth s Mantle

Parallel High-Order Geometric Multigrid Methods on Adaptive Meshes for Highly Heterogeneous Nonlinear Stokes Flow Simulations of Earth s Mantle ICES Student Forum The University of Texas at Austin, USA November 4, 204 Parallel High-Order Geometric Multigrid Methods on Adaptive Meshes for Highly Heterogeneous Nonlinear Stokes Flow Simulations of

More information

SU 2 : Advanced Analysis Topics

SU 2 : Advanced Analysis Topics SU 2 : Advanced Analysis Topics OpenMDAO-SU 2 Joint Workshop Stanford University Tuesday, October 1, 2013 Thomas D. Economon Department of Aeronautics & Astronautics Stanford University 1 Three Main Topics

More information

Accelerated flow acoustic boundary element solver and the noise generation of fish

Accelerated flow acoustic boundary element solver and the noise generation of fish Accelerated flow acoustic boundary element solver and the noise generation of fish JUSTIN W. JAWORSKI, NATHAN WAGENHOFFER, KEITH W. MOORED LEHIGH UNIVERSITY, BETHLEHEM, USA FLINOVIA PENN STATE 27 APRIL

More information

A MULTI-DOMAIN ALE ALGORITHM FOR SIMULATING FLOWS INSIDE FREE-PISTON DRIVEN HYPERSONIC TEST FACILITIES

A MULTI-DOMAIN ALE ALGORITHM FOR SIMULATING FLOWS INSIDE FREE-PISTON DRIVEN HYPERSONIC TEST FACILITIES A MULTI-DOMAIN ALE ALGORITHM FOR SIMULATING FLOWS INSIDE FREE-PISTON DRIVEN HYPERSONIC TEST FACILITIES Khalil Bensassi, and Herman Deconinck Von Karman Institute for Fluid Dynamics Aeronautics & Aerospace

More information

Aerodynamic Characteristics of Flapping Motion in Hover

Aerodynamic Characteristics of Flapping Motion in Hover Aerodynamic Characteristics of Flapping Motion in Hover D. Funda Kurtulus 1,4, Laurent David 2, Alain Farcy 3, Nafiz Alemdaroglu 4 1: LEA, ENSMA, Poitiers, France, dfunda@ae.metu.edu.tr 2: LEA, University

More information

Sharp-Interface Cartesian Method for Simulating Flow past 3D Flexible Bodies

Sharp-Interface Cartesian Method for Simulating Flow past 3D Flexible Bodies Sharp-Interface Cartesian Method for Simulating Flow past 3D Flexible Bodies ANVAR GILMANOV & FOTIS SOTIROPOULOS School of Civil and Environmental Engineering Georgia Institute of Technology Atlanta, GA

More information

Theory, Computation and Experiment on Criticality and Stability of Vortices Separating from Edges

Theory, Computation and Experiment on Criticality and Stability of Vortices Separating from Edges Theory, Computation and Experiment on Criticality and Stability of Vortices Separating from Edges Ashok Gopalarathnam Department of Mechanical and Aerospace Engineering North Carolina State University

More information

Computational Fluid Dynamics for Engineers

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

More information

Keywords: flows past a cylinder; detached-eddy-simulations; Spalart-Allmaras model; flow visualizations

Keywords: flows past a cylinder; detached-eddy-simulations; Spalart-Allmaras model; flow visualizations A TURBOLENT FLOW PAST A CYLINDER *Vít HONZEJK, **Karel FRAŇA *Technical University of Liberec Studentská 2, 461 17, Liberec, Czech Republic Phone:+ 420 485 353434 Email: vit.honzejk@seznam.cz **Technical

More information

Recent developments for the multigrid scheme of the DLR TAU-Code

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

More information

FLOW PAST A SQUARE CYLINDER CONFINED IN A CHANNEL WITH INCIDENCE ANGLE

FLOW PAST A SQUARE CYLINDER CONFINED IN A CHANNEL WITH INCIDENCE ANGLE International Journal of Mechanical Engineering and Technology (IJMET) Volume 9, Issue 13, December 2018, pp. 1642 1652, Article ID: IJMET_09_13_166 Available online at http://www.iaeme.com/ijmet/issues.asp?jtype=ijmet&vtype=9&itype=13

More information

The Immersed Interface Method

The Immersed Interface Method The Immersed Interface Method Numerical Solutions of PDEs Involving Interfaces and Irregular Domains Zhiiin Li Kazufumi Ito North Carolina State University Raleigh, North Carolina Society for Industrial

More information

Flow around a Suddenly Accelerated Rotating Plate at Low Reynolds Number

Flow around a Suddenly Accelerated Rotating Plate at Low Reynolds Number Flow around a Suddenly Accelerated Rotating Plate at Low Reynolds Number M. Percin 1,*, L. Ziegler 2, B. W. van Oudheusden 1 1: Faculty of Aerospace Engineering, Delft University of Technology, Delft,

More information

Solving Partial Differential Equations on Overlapping Grids

Solving Partial Differential Equations on Overlapping Grids **FULL TITLE** ASP Conference Series, Vol. **VOLUME**, **YEAR OF PUBLICATION** **NAMES OF EDITORS** Solving Partial Differential Equations on Overlapping Grids William D. Henshaw Centre for Applied Scientific

More information

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 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.

More information

SPC 307 Aerodynamics. Lecture 1. February 10, 2018

SPC 307 Aerodynamics. Lecture 1. February 10, 2018 SPC 307 Aerodynamics Lecture 1 February 10, 2018 Sep. 18, 2016 1 Course Materials drahmednagib.com 2 COURSE OUTLINE Introduction to Aerodynamics Review on the Fundamentals of Fluid Mechanics Euler and

More information

Simulation of Turbulent Flow in an Asymmetric Diffuser

Simulation of Turbulent Flow in an Asymmetric Diffuser Simulation of Turbulent Flow in an Asymmetric Diffuser 1. Purpose 58:160 Intermediate Mechanics of Fluids CFD LAB 3 By Tao Xing and Fred Stern IIHR-Hydroscience & Engineering The University of Iowa C.

More information

Finite Volume Discretization on Irregular Voronoi Grids

Finite Volume Discretization on Irregular Voronoi Grids Finite Volume Discretization on Irregular Voronoi Grids C.Huettig 1, W. Moore 1 1 Hampton University / National Institute of Aerospace Folie 1 The earth and its terrestrial neighbors NASA Colin Rose, Dorling

More information

SHOCK WAVES IN A CHANNEL WITH A CENTRAL BODY

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

More information

Chapter 7 Trailing and Leading Edge Flaps for Load Alleviation and Structure Control

Chapter 7 Trailing and Leading Edge Flaps for Load Alleviation and Structure Control Chapter 7 Trailing and Leading Edge Flaps for Load Alleviation and Structure Control Vladimir Leble and George N. Barakos Abstract This chapter presents the results of numerical computations for a 10-

More information

An Eulerian Immersed Boundary Method for Flow Simulations over Stationary and Moving Rigid Bodies

An Eulerian Immersed Boundary Method for Flow Simulations over Stationary and Moving Rigid Bodies An Eulerian Immersed Boundary for Flow Simulations over Stationary and Moving Rigid Bodies Evelise R. Corbalan Góis evelise@sc.usp.br University of São Paulo School of Engineering, São Carlos 13566-590

More information

Computational Fluid Dynamics Analysis of an Idealized Modern Wingsuit

Computational Fluid Dynamics Analysis of an Idealized Modern Wingsuit Washington University in St. Louis Washington University Open Scholarship Mechanical Engineering and Materials Science Independent Study Mechanical Engineering & Materials Science 12-21-2016 Computational

More information

A brief introduction to fluidstructure. O. Souček

A brief introduction to fluidstructure. O. Souček A brief introduction to fluidstructure interactions O. Souček Fluid-structure interactions Important class computational models Civil engineering Biomechanics Industry Geophysics From http://www.ihs.uni-stuttgart.de

More information

39th AIAA Aerospace Sciences Meeting and Exhibit January 8 11, 2001/Reno, NV

39th AIAA Aerospace Sciences Meeting and Exhibit January 8 11, 2001/Reno, NV AIAA 1 717 Static Aero-elastic Computation with a Coupled CFD and CSD Method J. Cai, F. Liu Department of Mechanical and Aerospace Engineering University of California, Irvine, CA 92697-3975 H.M. Tsai,

More information

Development of a Consistent Discrete Adjoint Solver for the SU 2 Framework

Development of a Consistent Discrete Adjoint Solver for the SU 2 Framework Development of a Consistent Discrete Adjoint Solver for the SU 2 Framework Tim Albring, Max Sagebaum, Nicolas Gauger Chair for Scientific Computing TU Kaiserslautern 16th Euro-AD Workshop, Jena December

More information

AN EXPERIMENTAL STUDY AND SIMULATION WITH FLUENT

AN EXPERIMENTAL STUDY AND SIMULATION WITH FLUENT AN EXPERIMENTAL STUDY AND SIMULATION WITH FLUENT OF THE HORIZONTAL AXIS WIND TURBINE (HAWT) BLADE TOWER DYNAMIC INTERACTION V. P. CAMBANIS 1 & H. STAPOUNTZIS 2 Lab. of Fluid Mechanics & Turbomachinery,

More information

Numerical Methods in Aerodynamics. Fluid Structure Interaction. Lecture 4: Fluid Structure Interaction

Numerical Methods in Aerodynamics. Fluid Structure Interaction. Lecture 4: Fluid Structure Interaction Fluid Structure Interaction Niels N. Sørensen Professor MSO, Ph.D. Department of Civil Engineering, Alborg University & Wind Energy Department, Risø National Laboratory Technical University of Denmark

More information

Introduction to Aerodynamic Shape Optimization

Introduction to Aerodynamic Shape Optimization Introduction to Aerodynamic Shape Optimization 1. Aircraft Process 2. Aircraft Methods a. Inverse Surface Methods b. Inverse Field Methods c. Numerical Optimization Methods Aircraft Process Conceptual

More information

Application of STAR-CCM+ to Helicopter Rotors in Hover

Application of STAR-CCM+ to Helicopter Rotors in Hover Application of STAR-CCM+ to Helicopter Rotors in Hover Lakshmi N. Sankar and Chong Zhou School of Aerospace Engineering, Georgia Institute of Technology, Atlanta, GA Ritu Marpu Eschol CD-Adapco, Inc.,

More information

Potsdam Propeller Test Case (PPTC)

Potsdam Propeller Test Case (PPTC) Second International Symposium on Marine Propulsors smp 11, Hamburg, Germany, June 2011 Workshop: Propeller performance Potsdam Propeller Test Case (PPTC) Olof Klerebrant Klasson 1, Tobias Huuva 2 1 Core

More information

High-Order Numerical Algorithms for Steady and Unsteady Simulation of Viscous Compressible Flow with Shocks (Grant FA )

High-Order Numerical Algorithms for Steady and Unsteady Simulation of Viscous Compressible Flow with Shocks (Grant FA ) High-Order Numerical Algorithms for Steady and Unsteady Simulation of Viscous Compressible Flow with Shocks (Grant FA9550-07-0195) Sachin Premasuthan, Kui Ou, Patrice Castonguay, Lala Li, Yves Allaneau,

More information

CFD-1. Introduction: What is CFD? T. J. Craft. Msc CFD-1. CFD: Computational Fluid Dynamics

CFD-1. Introduction: What is CFD? T. J. Craft. Msc CFD-1. CFD: Computational Fluid Dynamics School of Mechanical Aerospace and Civil Engineering CFD-1 T. J. Craft George Begg Building, C41 Msc CFD-1 Reading: J. Ferziger, M. Peric, Computational Methods for Fluid Dynamics H.K. Versteeg, W. Malalasekara,

More information

Performance of Implicit Solver Strategies on GPUs

Performance of Implicit Solver Strategies on GPUs 9. LS-DYNA Forum, Bamberg 2010 IT / Performance Performance of Implicit Solver Strategies on GPUs Prof. Dr. Uli Göhner DYNAmore GmbH Stuttgart, Germany Abstract: The increasing power of GPUs can be used

More information

Numerical Study of Applications of Active Flow Control for Drag Reduction

Numerical Study of Applications of Active Flow Control for Drag Reduction Numerical Study of Applications of Active Flow Control for Drag Reduction RAMESH K. AGARWAL Department of Mechanical Engineering and Materials Science Washington University in St. Louis 1 Brookings Drive,

More information

Modeling a Nozzle in a Borehole

Modeling a Nozzle in a Borehole Modeling a Nozzle in a Borehole E. Holzbecher, F. Sun Georg-August Universität Göttingen *Goldschmidtstr. 3, 37077 Göttingen, GERMANY; E-mail: eholzbe@gwdg.de Abstract: A nozzle, installed in an injecting

More information

SELECTIVE ALGEBRAIC MULTIGRID IN FOAM-EXTEND

SELECTIVE ALGEBRAIC MULTIGRID IN FOAM-EXTEND Student Submission for the 5 th OpenFOAM User Conference 2017, Wiesbaden - Germany: SELECTIVE ALGEBRAIC MULTIGRID IN FOAM-EXTEND TESSA UROIĆ Faculty of Mechanical Engineering and Naval Architecture, Ivana

More information

How to Enter and Analyze a Wing

How to Enter and Analyze a Wing How to Enter and Analyze a Wing Entering the Wing The Stallion 3-D built-in geometry creation tool can be used to model wings and bodies of revolution. In this example, a simple rectangular wing is modeled

More information

Aeroacoustic computations with a new CFD solver based on the Lattice Boltzmann Method

Aeroacoustic computations with a new CFD solver based on the Lattice Boltzmann Method Aeroacoustic computations with a new CFD solver based on the Lattice Boltzmann Method D. Ricot 1, E. Foquet 2, H. Touil 3, E. Lévêque 3, H. Machrouki 4, F. Chevillotte 5, M. Meldi 6 1: Renault 2: CS 3:

More information