UWE has obtained warranties from all depositors as to their title in the material deposited and as to their right to deposit such material.
|
|
- Angela Green
- 5 years ago
- Views:
Transcription
1 Yao, Y., Fang, J., Zheltovodov, A. A. and Lu, L. (2014) Direct numerical simulation of supersonic flows passing a backward step. In: UK Turbulence Consortium Workshop, Imperial College, London, September Available from: We recommend you cite the published version. The publisher s URL is: Refereed: Yes (no note) Disclaimer UWE has obtained warranties from all depositors as to their title in the material deposited and as to their right to deposit such material. UWE makes no representation or warranties of commercial utility, title, or fitness for a particular purpose or any other warranty, express or implied in respect of any material deposited. UWE makes no representation that the use of the materials will not infringe any patent, copyright, trademark or other property or proprietary rights. UWE accepts no liability for any infringement of intellectual property rights in any material deposited but will remove such material from public view pending investigation in the event of an allegation of any such infringement. PLEASE SCROLL DOWN FOR TEXT.
2 UK Turbulence Consortium Workshop Sept, 2014 Direct Numerical Simulation of Supersonic Flows Passing a Backward Step Jian Fang, Yufeng Yao, Alexander A. Zheltovodov, Lipeng Lu
3 Problem Background Supersonic flow passing a Backward step is one of key flow phenomena in high-speed vehicle and its propulsion systems Fully developed turbulent flow Expansion fan Shock-wave
4 E(k) CFD code: Low-Dissipation Monotonicity-Preserving Scheme Bandwidth dissipation optimization method (BDOM) is used to optimize the linear part of the MP scheme 1. Fang, J., Li, Z. and Lu, L., Journal of Scientific Computing, 56:67-95, Fang, J., Yao, Y.F., Li, Z. and Lu, L., Computers and Fluids, 104: 55-72, =1/280 =0.9/ =0.8/280 1E-3 =0.7/280 k -5/3 k st order upwind scheme 3rd order upwind scheme 5th order upwind scheme 7th order upwind scheme Eq. (3.11) with different k =0.6/280 =0.5/280 =0.4/280 =0.3/280 =0.2/280 =0.1/280 =0/280 1E-4 1E-5 1E-6 Reference COMP6 MP7-LD MP7 WENO7-Z MP5-LD MP5 WENO5-Z 1 10 k Bandwidth property of MP7-LD scheme DNS of isotropic turbulence
5 Supersonic flow passing a backward step 25 Mach=2.9 Case 1: Re d =20000 Case 2: Re d =40000 Case 3: Re d =80000 Density Schlieren Pressure Field Ref: Zheltovodov, A., et al. (1990). An Experimental Documentation of Supersonic Turbulent Flows in the Vicinity of Forward and Backward-Facing Ramps.
6 Separation bubble reduces with Reynolds number Mean Streamlines Re=20000 Re=40000 Re=80000
7 Surface pressure and skin friction Cf PW/P EC CC x Wall Pressure Case 1 Case 2 Case 3 Experiment at Re d = Experiment at Re d =80000 Experiment at Re d =67600 Experiment at Re d =40700 LES of El-Askary 2011 LES of Knight et al EC: expansion corner; CC: compression corner EC CC x Skin friction Case 1 Case 2 Case 3 LES of El-Askary 2011 LES of Knight et al Experiment at Re d = Experiment at Re d =80000 Ref : Zheltovodov, A., et al. (1990). An Experimental Documentation of Supersonic Turbulent Flows in the Vicinity of Forward and Backward-Facing Ramps.
8 dpw/dx Pressure gradient and numerical Schlieren Peak 2 (r) Peak 1 (s) Separation point (s) Case 1 Case EC CC x Wall Pressure Gradient Schematic draw of separation length Re=20000 Re=40000 Re=80000
9 d Turbulent flow properties and its variation =2 =5 =6 =7 =8 =9 =11 =12 =15 =20 =23 Turbulence Kinetic Energy Reynolds Shear Stress < u v > =x EC =x CC K Peak location change lifted during separation
10 K Variation along two streamlines <u''v''> S1: near wall S2: mid-bl at inflow S1 S2 8 6 EC CC S1 S EC CC S1 S long plateau x short plateau Different evolution process of TKE and Reynolds shear stress along two streamlines x
11 Variation of cross correlation d R(us'',un'') Correlation of streamwise and normal velocity fluctuation
12 Locations for comparison Location of correlation peaks
13 Instantaneous streamwise u Streamwise velocity fluctuation along the streamlines S1 and S2
14 Finer flow structures Classic horseshoe wall turbulence Suppression of Turbulence DNS of Zhou et al Large-scale Görtler Vortex Iso-surface of l ci colored with w x Turbulent Coherent Structure Iso-surface of w colored with u x
15 Close view of flow structures Horseshoe vortex Turbulent coherent structures in the ramp region
16 Flow topology compared to Oil-flow test Time mean wall streamline and skin friction Oil-flow visualization (Zheltovodov et al., 1983)
17 Surface flow topology d d Re=20000 Re=40000 d Distance between neighbour nodes = BL thickness δ Re=80000
18 Concluding Remarks Supersonic Expansion/Compression Corner is investigated by using DNS Turbulence is suppressed during expansion but enhanced in compression; Two different characteristics of turbulent structures was found in the ramp region as In the outer layer, turbulence is consistently suppressed; In the inner layer, (1) turbulence is largely suppressed only in the corner region, then gradually redevelops; (2) coherence structure of fluctuations is preserved and it increases during the compression Large-scale Görtler vortices are clearly captured, indicating its connection to upstream wall turbulence; Reynolds number effect is observed Separation bubble shrinks with the increase of Re, but Scale of Görtler vortices is independent of Re (distance between nodes)
19 Thank You!
We recommend you cite the published version. The publisher s URL is:
Fang, J., Yao, Y., Li, Z. and Lu, L. (2014) Investigation of lowdissipation monotonicity-preserving scheme for direct numerical simulation of compressible turbulent flows. Computers & Fluids, 104. pp.
More informationAnalysis of Shock Motion in STBLI Induced by a Compression Ramp Configuration Using DNS Data
45th AIAA Aerospace Science Meeting and Exhibit, January 8 11, 25/Reno, Nevada Analysis of Shock Motion in STBLI Induced by a Compression Ramp Configuration Using DNS Data M. Wu and M.P. Martin Mechanical
More informationNew DNS Results of Shockwave/Turbulent Boundary Layer Interaction
36th AIAA Fluid Dynamics Conference, June 5 8, 26/San Francisco,California New DNS Results of Shockwave/Turbulent Boundary Layer Interaction M. Wu and M.P. Martin Mechanical and Aerospace Engineering Department
More informationLES Study of Shock Wave and Turbulent Boundary Layer Interaction
51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 07-10 January 2013, Grapevine (Dallas/Ft. Worth Region), Texas AIAA 2013-0984 LES Study of Shock Wave and
More informationNumerical Investigation of Shock wave Turbulent Boundary Layer Interaction over a 2D Compression Ramp
Advances in Aerospace Science and Applications. ISSN 2277-3223 Volume 4, Number 1 (2014), pp. 25-32 Research India Publications http://www.ripublication.com/aasa.htm Numerical Investigation of Shock wave
More informationPreliminary Study of the Turbulence Structure in Supersonic Boundary Layers using DNS Data
35th AIAA Fluid Dynamics Conference, June 6 9, 2005/Toronto,Canada Preliminary Study of the Turbulence Structure in Supersonic Boundary Layers using DNS Data Ellen M. Taylor, M. Pino Martín and Alexander
More informationWALL ROUGHNESS EFFECTS ON SHOCK BOUNDARY LAYER INTERACTION FLOWS
ISSN (Online) : 2319-8753 ISSN (Print) : 2347-6710 International Journal of Innovative Research in Science, Engineering and Technology An ISO 3297: 2007 Certified Organization, Volume 2, Special Issue
More informationcompression corner flows with high deflection angle, for example, the method cannot predict the location
4nd AIAA Aerospace Sciences Meeting and Exhibit 5-8 January 4, Reno, Nevada Modeling the effect of shock unsteadiness in shock-wave/ turbulent boundary layer interactions AIAA 4-9 Krishnendu Sinha*, Krishnan
More informationNumerical and Experimental Study on the Effect of Guide Vane Insertion on the Flow Characteristics in a 90º Rectangular Elbow
Numerical and Experimental Study on the Effect of Guide Vane Insertion on the Flow Characteristics in a 90º Rectangular Elbow Sutardi 1, Wawan A. W., Nadia, N. and Puspita, K. 1 Mechanical Engineering
More informationZonal hybrid RANS-LES modeling using a Low-Reynolds-Number k ω approach
Zonal hybrid RANS-LES modeling using a Low-Reynolds-Number k ω approach S. Arvidson 1,2, L. Davidson 1, S.-H. Peng 1,3 1 Chalmers University of Technology 2 SAAB AB, Aeronautics 3 FOI, Swedish Defence
More informationConvection in Three-Dimensional Separated and Attached Flow
Convection in Three-Dimensional Separated and Attached Flow B. F. Armaly Convection Heat Transfer Laboratory Department of Mechanical and Aerospace Engineering, and Engineering Mechanics University of
More informationExplicit algebraic Reynolds stress models for internal flows
5. Double Circular Arc (DCA) cascade blade flow, problem statement The second test case deals with a DCA compressor cascade, which is considered a severe challenge for the CFD codes, due to the presence
More informationCFD Analysis of Micro-Ramps for Hypersonic Flows Mogrekar Ashish 1, a, Sivakumar, R. 2, b
Applied Mechanics and Materials Submitted: 2014-04-25 ISSN: 1662-7482, Vols. 592-594, pp 1962-1966 Revised: 2014-05-07 doi:10.4028/www.scientific.net/amm.592-594.1962 Accepted: 2014-05-16 2014 Trans Tech
More informationANALYSIS OF SHOCK MOTION IN STBLI USING DNS DATA
ANALYSIS OF SHOCK MOTION IN STBLI USING DNS DATA Minwei Wu and Pino Martin Department of Mechanical and Aerospace Engineering, Princeton University, Princeton, NJ 8544, USA * Abstract Direct numerical
More information1. For an ideal gas, internal energy is considered to be a function of only. YOUR ANSWER: Temperature
CHAPTER 11 1. For an ideal gas, internal energy is considered to be a function of only. YOUR ANSWER: Temperature 2.In Equation 11.7 the subscript p on the partial derivative refers to differentiation at
More informationSIMULATION OF THREE-DIMENSIONAL INCOMPRESSIBLE CAVITY FLOWS
ICAS 2000 CONGRESS SIMULATION OF THREE-DIMENSIONAL INCOMPRESSIBLE CAVITY FLOWS H Yao, R K Cooper, and S Raghunathan School of Aeronautical Engineering The Queen s University of Belfast, Belfast BT7 1NN,
More informationThere are no simple turbulent flows
Turbulence 1 There are no simple turbulent flows Turbulent boundary layer: Instantaneous velocity field (snapshot) Ref: Prof. M. Gad-el-Hak, University of Notre Dame Prediction of turbulent flows standard
More informationThe Computations of Jet Interaction on a Generic Supersonic Missile
The Computations of Jet Interaction on a Generic Supersonic Missile *Jinbum Huh 1) and Seungsoo Lee 2) 1), 2) Department of Aerospace Engineering, Inha Univ., Incheon, Korea 2) slee@inha.ac.kr ABSTRACT
More informationDESIGN & COMPUTATIONAL FLUID DYNAMICS ANALYSES OF AN AXISYMMETRIC NOZZLE AT TRANSONIC FREE STREAM CONDITIONS
DESIGN & COMPUTATIONAL FLUID DYNAMICS ANALYSES OF AN AXISYMMETRIC NOZZLE AT TRANSONIC FREE STREAM CONDITIONS S Wasim Akram 1, S. Rajesh 2 1 M.Tech Student, Department of Mechanical Engineering, Krishna
More informationComputational fluid dynamics study of flow depth in an open Venturi channel for Newtonian fluid
Computational fluid dynamics study of flow depth in an open Venturi channel for Newtonian fluid Prasanna Welahettige 1, Bernt Lie 1, Knut Vaagsaether 1 1 Department of Process, Energy and Environmental
More informationFINAL REPORT. Office of Naval Research. entitled. Anatol Roshko Theodore Von Karman Professor of Aeronautics
to F11 F rnpv FINAL REPORT 4to Office of Naval Research on Contract No. N00014-85-C-0646 Work Unit No. 4328-434 entitled STRUCTURE AND MIXING IN TURBULENT SHEAR FLOWS 1 July 1985-31 October 1988 Anatol
More informationStudies on the Transition of the Flow Oscillations over an Axisymmetric Open Cavity Model
Advances in Aerospace Science and Applications. ISSN 2277-3223 Volume 3, Number 2 (2013), pp. 83-90 Research India Publications http://www.ripublication.com/aasa.htm Studies on the Transition of the Flow
More informationFACULTY OF CHEMICAL & ENERGY ENGINEERING FLUID MECHANICS LABORATORY TITLE OF EXPERIMENT: MINOR LOSSES IN PIPE (E4)
FACULTY OF CHEMICAL & ENERGY ENGINEERING FLUID MECHANICS LABORATORY TITLE OF EXPERIMENT: MINOR LOSSES IN PIPE (E4) 1 1.0 Objectives The objective of this experiment is to calculate loss coefficient (K
More informationDay 24: Flow around objects
Day 24: Flow around objects case 1) fluid flowing around a fixed object (e.g. bridge pier) case 2) object travelling within a fluid (cars, ships planes) two forces are exerted between the fluid and the
More informationTurbulent boundary layer
Turbulent boundary layer 0. Are they so different from laminar flows? 1. Three main effects of a solid wall 2. Statistical description: equations & results 3. Mean velocity field: classical asymptotic
More informationInternational Conference on Methods of Aerophysical Research, ICMAR 2008
International Conference on Methods of Aerophysical Research, ICMAR 8 EXPERIMENTAL STUDY OF UNSTEADY EFFECTS IN SHOCK WAVE / TURBULENT BOUNDARY LAYER INTERACTION P.A. Polivanov, А.А. Sidorenko, A.A. Maslov
More informationNumerical investigation of swirl flow inside a supersonic nozzle
Advances in Fluid Mechanics IX 131 Numerical investigation of swirl flow inside a supersonic nozzle E. Eslamian, H. Shirvani & A. Shirvani Faculty of Science and Technology, Anglia Ruskin University, UK
More informationGPPS NUMERICAL PREDICTION OF UNSTEADY ENDWALL FLOW AND HEAT TRANSFER WITH ONCOMING WAKE
Proceedings of Shanghai 17 Global Power and Propulsion Forum 3 th October 1 st November, 17 http://www.gpps.global GPPS-17-133 NUMERICAL PREDICTION OF UNSTEADY ENDWALL FLOW AND HEAT TRANSFER WITH ONCOMING
More informationNumerical Studies of Supersonic Jet Impingement on a Flat Plate
Numerical Studies of Supersonic Jet Impingement on a Flat Plate Overset Grid Symposium Dayton, OH Michael R. Brown Principal Engineer, Kratos/Digital Fusion Solutions Inc., Huntsville, AL. October 18,
More informationIntroduction to Turbulence AEEM Why study turbulent flows?
Introduction to Turbulence AEEM 7063-003 Dr. Peter J. Disimile UC-FEST Department of Aerospace Engineering Peter.disimile@uc.edu Intro to Turbulence: C1A Why 1 Most flows encountered in engineering and
More informationDefense Technical Information Center Compilation Part Notice
UNCLASSIFIED Defense Technical Information Center Compilation Part Notice ADP013688 TITLE: Large-Eddy Simulation of Mach 3.0 Flow Past a 24-Degree Compression Ramp DISTRIBUTION: Approved for public release,
More informationCOMPUTATIONAL SIMULATION OF THE FLOW PAST AN AIRFOIL FOR AN UNMANNED AERIAL VEHICLE
COMPUTATIONAL SIMULATION OF THE FLOW PAST AN AIRFOIL FOR AN UNMANNED AERIAL VEHICLE L. Velázquez-Araque 1 and J. Nožička 2 1 Division of Thermal fluids, Department of Mechanical Engineering, National University
More informationAnalysis of shock motion in shockwave and turbulent boundary layer interaction using direct numerical simulation data
J. Fluid Mech. (8), vol. 594, pp. 7 8. c 8 Cambridge University Press doi:.7/s7944 Printed in the United Kingdom 7 Analysis of shock motion in shockwave and turbulent boundary layer interaction using direct
More informationTurbulence Modeling I!
Outline! Turbulence Modeling I! Grétar Tryggvason! Spring 2010! Why turbulence modeling! Reynolds Averaged Numerical Simulations! Zero and One equation models! Two equations models! Model predictions!
More informationDNS STUDY OF TURBULENT HEAT TRANSFER IN A SPANWISE ROTATING SQUARE DUCT
10 th International Symposium on Turbulence and Shear Flow Phenomena (TSFP10), Chicago, USA, July, 2017 DNS STUDY OF TURBULENT HEAT TRANSFER IN A SPANWISE ROTATING SQUARE DUCT Bing-Chen Wang Department
More informationNumerical Investigation of the Fluid Flow around and Past a Circular Cylinder by Ansys Simulation
, pp.49-58 http://dx.doi.org/10.1457/ijast.016.9.06 Numerical Investigation of the Fluid Flow around and Past a Circular Cylinder by Ansys Simulation Mojtaba Daneshi Department of Mechanical Engineering,
More information58:160 Intermediate Fluid Mechanics Bluff Body Professor Fred Stern Fall 2014
Professor Fred Stern Fall 04 Chapter 7 Bluff Body Fluid flows are broadly categorized:. Internal flows such as ducts/pipes, turbomachinery, open channel/river, which are bounded by walls or fluid interfaces:
More informationInvestigation of reattachment length for a turbulent flow over a backward facing step for different step angle
MultiCraft International Journal of Engineering, Science and Technology Vol. 3, No. 2, 2011, pp. 84-88 INTERNATIONAL JOURNAL OF ENGINEERING, SCIENCE AND TECHNOLOGY www.ijest-ng.com 2011 MultiCraft Limited.
More informationDirect Numerical Simulation of Pressure Fluctuations Induced by Supersonic Turbulent Boundary Layers
Direct Numerical Simulation of Pressure Fluctuations Induced by Supersonic Turbulent Boundary Layers PI: Lian Duan --- NSF PRAC 1640865- --- Missouri U. of S&T Project Members: Chao Zhang, Junji Huang,
More informationColloquium FLUID DYNAMICS 2013 Institute of Thermomechanics AS CR, v.v.i., Prague, October 23-25, 2013 p.1
Colloquium FLUID DYNAMICS 2013 Institute of Thermomechanics AS CR, v.v.i., Prague, October 23-25, 2013 p.1 ON THE REYNOLDS NUMBER ROLE IN STRUCTURE OF RECIRCULATION ZONE BEHIND BACKWARD FACING STEP IN
More informationDEVELOPMENT OF CFD MODEL FOR A SWIRL STABILIZED SPRAY COMBUSTOR
DRAFT Proceedings of ASME IMECE: International Mechanical Engineering Conference & Exposition Chicago, Illinois Nov. 5-10, 2006 IMECE2006-14867 DEVELOPMENT OF CFD MODEL FOR A SWIRL STABILIZED SPRAY COMBUSTOR
More informationFEDSM COMPUTATIONAL AEROACOUSTIC ANALYSIS OF OVEREXPANDED SUPERSONIC JET IMPINGEMENT ON A FLAT PLATE WITH/WITHOUT HOLE
Proceedings of FEDSM2007: 5 th Joint ASME/JSME Fluids Engineering Conference July 30-August 2, 2007, San Diego, CA, USA FEDSM2007-37563 COMPUTATIONAL AEROACOUSTIC ANALYSIS OF OVEREXPANDED SUPERSONIC JET
More informationCFD Study of Flow Over Parallel Ridges with Varying Height and Spacing
Proceedings of the World Congress on Engineering 21 Vol II WCE 21, June 3 - July 2, 21, London, U.K. CFD Study of Flow Over Parallel Ridges with Varying Height and Spacing Lee Chin Yik, Salim Mohamed Salim,
More informationCurriculum Vitae of Sergio Pirozzoli
Curriculum Vitae of Sergio Pirozzoli Address University of Rome La Sapienza Department of Mechanical and Aerospace Engineering Via Eudossiana 18 00184, Roma Contact tel.: +39 06 44585202 fax : +39 06 4881759
More informationTurbulent eddies in the RANS/LES transition region
Turbulent eddies in the RANS/LES transition region Ugo Piomelli Senthil Radhakrishnan Giuseppe De Prisco University of Maryland College Park, MD, USA Research sponsored by the ONR and AFOSR Outline Motivation
More informationUWE has obtained warranties from all depositors as to their title in the material deposited and as to their right to deposit such material.
Khali, E. H. and Yao, Y. (2015) Mixing flow characteristics for a transverse sonic jet injecting into a supersonic crossflow. In: 53rd AIAA Aerospace Sciences Meeting: AIAA 2015 Sci-Tech Conference, Kissimmee,
More informationINSTITUTTET FOR BYGNINGSTEKNIK DEPT. OF BUILDING TECHNOLOGY AND STRUCTURAL ENGINEERING AALBORG UNIVERSITET AAU AALBORG DANMARK
INSTITUTTET FOR BYGNINGSTEKNIK DEPT. OF BUILDING TECHNOLOGY AND STRUCTURAL ENGINEERING AALBORG UNIVERSITET AAU AALBORG DANMARK Lars Davidson and Peter V. Nielsen A Study of Laminar Backward-Facing Step
More informationTurbulence. 2. Reynolds number is an indicator for turbulence in a fluid stream
Turbulence injection of a water jet into a water tank Reynolds number EF$ 1. There is no clear definition and range of turbulence (multi-scale phenomena) 2. Reynolds number is an indicator for turbulence
More informationNumerical Investigation of the Transonic Base Flow of A Generic Rocket Configuration
1 Numerical Investigation of the Transonic Base Flow of A Generic Rocket Configuration A. Henze, C. Glatzer, M. Meinke, W. Schröder Institute of Aerodynamics, RWTH Aachen University, Germany March 21,
More informationDetached Eddy Simulation on Hypersonic Base Flow Structure of Reentry-F Vehicle
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,
More informationBasic Features of the Fluid Dynamics Simulation Software FrontFlow/Blue
11 Basic Features of the Fluid Dynamics Simulation Software FrontFlow/Blue Yang GUO*, Chisachi KATO** and Yoshinobu YAMADE*** 1 FrontFlow/Blue 1) is a general-purpose finite element program that calculates
More informationLarge-eddy simulations for wind turbine blade: rotational augmentation and dynamic stall
Large-eddy simulations for wind turbine blade: rotational augmentation and dynamic stall Y. Kim, I.P. Castro, and Z.T. Xie Introduction Wind turbines operate in the atmospheric boundary layer and their
More informationProspects for High-Speed Flow Simulations
Prospects for High-Speed Flow Simulations Graham V. Candler Aerospace Engineering & Mechanics University of Minnesota Support from AFOSR and ASDR&E Future Directions in CFD Research: A Modeling & Simulation
More informationIMAGE-BASED MODELING OF THE SKIN-FRICTION COEFFICIENT IN COMPRESSIBLE BOUNDARY-LAYER TRANSITION
IMAGE-BASED MODELING OF THE SKIN-FRICTION COEFFICIENT IN COMPRESSIBLE BOUNDARY-LAYER TRANSITION Wenjie Zheng State Key Laboratory of Turbulence and Complex Systems College of Engineering, Peking University
More information41st Aerospace Sciences Meeting and Exhibit 6-9 January 2003, Reno, Nevada Modeling shock unsteadiness in shock/turbulence interaction
4st Aerospace Sciences Meeting and Exhibit 6-9 January 003, Reno, Nevada Modeling shock unsteadiness in shock/turbulence interaction AIAA 003-65 Krishnendu Sinha*, Krishnan Mahesh and Graham V. Candler
More informationComputational Investigations of High-Speed Dual-Stream Jets
9th AIAA/CEAS Aeroacoustics Conference and Exhibit -4 May 3, Hilton Head, South Carolina AIAA 3-33 Computational Investigations of High-Speed Dual-Stream Jets Nicholas J. Georgiadis * National Aeronautics
More informationMelbourne, Victoria, 3010, Australia. To link to this article:
This article was downloaded by: [The University Of Melbourne Libraries] On: 18 October 2012, At: 21:54 Publisher: Taylor & Francis Informa Ltd Registered in England and Wales Registered Number: 1072954
More informationNumerical Investigations of the Effects of Sidewall Compression and Relaminarization in 3D Scramjet Inlet
17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 11-14 April 2011, San Francisco, California AIAA 2011-2256 Numerical Investigations of the Effects of Sidewall Compression
More informationGeneration of initial fields for channel flow investigation
Generation of initial fields for channel flow investigation Markus Uhlmann Potsdam Institut für Klimafolgenforschung, D-442 Potsdam uhlmann@pik-potsdam.de (Mai 2) In the framework of the DFG-funded research
More information1. Introduction, tensors, kinematics
1. Introduction, tensors, kinematics Content: Introduction to fluids, Cartesian tensors, vector algebra using tensor notation, operators in tensor form, Eulerian and Lagrangian description of scalar and
More informationIntroduction to Aerodynamics. Dr. Guven Aerospace Engineer (P.hD)
Introduction to Aerodynamics Dr. Guven Aerospace Engineer (P.hD) Aerodynamic Forces All aerodynamic forces are generated wither through pressure distribution or a shear stress distribution on a body. The
More informationIntroduction and Basic Concepts
Topic 1 Introduction and Basic Concepts 1 Flow Past a Circular Cylinder Re = 10,000 and Mach approximately zero Mach = 0.45 Mach = 0.64 Pictures are from An Album of Fluid Motion by Van Dyke Flow Past
More informationBasic Fluid Mechanics
Basic Fluid Mechanics Chapter 6A: Internal Incompressible Viscous Flow 4/16/2018 C6A: Internal Incompressible Viscous Flow 1 6.1 Introduction For the present chapter we will limit our study to incompressible
More informationSG Turbulence models for CFD
SG2218 2012 Turbulence models for CFD Stefan Wallin Linné FLOW Centre Dept of Mechanics, KTH Dept. of Aeronautics and Systems Integration, FOI There are no simple turbulent flows Turbulent boundary layer:
More informationPredictive Inner-Outer Model for Turbulent Boundary Layers Applied to Hypersonic DNS Data
51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 07-10 January 2013, Grapevine (Dallas/Ft. Worth Region), Texas AIAA 2013-0265 Predictive Inner-Outer Model
More informationModelling of Gas-Solid Flows with Non-spherical Particles
Imperial College London Department of Mechanical Engineering Exhibition Road London, SW7 AZ Modelling of Gas-Solid Flows with Non-spherical Particles Fan Zhao MSc September 014 Supervised by Dr Berend
More informationProcess Chemistry Toolbox - Mixing
Process Chemistry Toolbox - Mixing Industrial diffusion flames are turbulent Laminar Turbulent 3 T s of combustion Time Temperature Turbulence Visualization of Laminar and Turbulent flow http://www.youtube.com/watch?v=kqqtob30jws
More informationTURBINE BURNERS: Engine Performance Improvements; Mixing, Ignition, and Flame-Holding in High Acceleration Flows
TURBINE BURNERS: Engine Performance Improvements; Mixing, Ignition, and Flame-Holding in High Acceleration Flows Presented by William A. Sirignano Mechanical and Aerospace Engineering University of California
More informationMULTIDIMENSIONAL TURBULENCE SPECTRA - STATISTICAL ANALYSIS OF TURBULENT VORTICES
Ninth International Conference on CFD in the Minerals and Process Industries CSIRO, Melbourne, Australia 10-12 December 2012 MULTIDIMENSIONAL TURBULENCE SPECTRA - STATISTICAL ANALYSIS OF TURBULENT VORTICES
More informationDivergence free synthetic eddy method for embedded LES inflow boundary condition
R. Poletto*, A. Revell, T. Craft, N. Jarrin for embedded LES inflow boundary condition University TSFP Ottawa 28-31/07/2011 *email: ruggero.poletto@postgrad.manchester.ac.uk 1 / 19 SLIDES OVERVIEW 1 Introduction
More informationChapter 5 Phenomena of laminar-turbulent boundary layer transition (including free shear layers)
Chapter 5 Phenomena of laminar-turbulent boundary layer transition (including free shear layers) T-S Leu May. 3, 2018 Chapter 5: Phenomena of laminar-turbulent boundary layer transition (including free
More informationDirect Numerical Simulations of Transitional Flow in Turbomachinery
Direct Numerical Simulations of Transitional Flow in Turbomachinery J.G. Wissink and W. Rodi Institute for Hydromechanics University of Karlsruhe Unsteady transitional flow over turbine blades Periodic
More informationMysteries of Engineering Fluid Mechanics
Mysteries of Engineering Fluid Mechanics Gordon D. Stubley Mechanical Engineering Department University of Waterloo Waterloo ON N2L 3G1 CANADA email: stubley@uwaterloo.ca November 30, 2003 2 Contents 1
More informationTurbulent Boundary Layers & Turbulence Models. Lecture 09
Turbulent Boundary Layers & Turbulence Models Lecture 09 The turbulent boundary layer In turbulent flow, the boundary layer is defined as the thin region on the surface of a body in which viscous effects
More informationApplied Mathematics and Mechanics (English Edition) Non-equilibrium turbulent phenomena in the flow over a backward-facing ramp
Appl. Math. Mech. -Engl. Ed., 40(2), 215 236 (2019) Applied Mathematics and Mechanics (English Edition) https://doi.org/10.1007/s10483-019-2428-6 Non-equilibrium turbulent phenomena in the flow over a
More informationExternal Flow and Boundary Layer Concepts
1 2 Lecture (8) on Fayoum University External Flow and Boundary Layer Concepts By Dr. Emad M. Saad Mechanical Engineering Dept. Faculty of Engineering Fayoum University Faculty of Engineering Mechanical
More informationChapter 3 Lecture 8. Drag polar 3. Topics. Chapter-3
Chapter 3 ecture 8 Drag polar 3 Topics 3.2.7 Boundary layer separation, adverse pressure gradient and favourable pressure gradient 3.2.8 Boundary layer transition 3.2.9 Turbulent boundary layer over a
More informationThe Simulation of Wraparound Fins Aerodynamic Characteristics
The Simulation of Wraparound Fins Aerodynamic Characteristics Institute of Launch Dynamics Nanjing University of Science and Technology Nanjing Xiaolingwei 00 P. R. China laithabbass@yahoo.com Abstract:
More informationApplied Mathematics and Mechanics (English Edition)
Appl. Math. Mech. -Engl. Ed., 39(9), 1267 1276 (2018) Applied Mathematics and Mechanics (English Edition) https://doi.org/10.1007/s10483-018-2364-7 Direct numerical simulation of turbulent flows through
More informationEFFECT OF REYNOLDS NUMBER ON THE UNSTEADY FLOW AND ACOUSTIC FIELDS OF SUPERSONIC CAVITY
Proceedings of FEDSM 03 4TH ASME_JSME Joint Fluids Engineering Conference Honolulu, Hawaii, USA, July 6 11, 2003 FEDSM2003-45473 EFFECT OF REYNOLDS NUMBER ON THE UNSTEADY FLOW AND ACOUSTIC FIELDS OF SUPERSONIC
More information1. Introduction Some Basic Concepts
1. Introduction Some Basic Concepts 1.What is a fluid? A substance that will go on deforming in the presence of a deforming force, however small 2. What Properties Do Fluids Have? Density ( ) Pressure
More informationof Shock Wave Turbulent Boundary
I AlAA 91-0651 Visualization of the Structure of Shock Wave Turbulent Boundary Layer Interactions using Rayleigh Scattering D. R. Smith, J. Poggie, W. Konrad and A. J. Smits Princeton University Princeton,
More informationFLOW-NORDITA Spring School on Turbulent Boundary Layers1
Jonathan F. Morrison, Ati Sharma Department of Aeronautics Imperial College, London & Beverley J. McKeon Graduate Aeronautical Laboratories, California Institute Technology FLOW-NORDITA Spring School on
More informationAerodynamic Optimization of the Expansion Section in a Hypersonic Quiet Nozzle Based on Favorable Pressure Effect
Journal of Applied Mathematics and Physics, 2014, 2, 443-448 Published Online May 2014 in SciRes. http://www.scirp.org/journal/jamp http://dx.doi.org/10.4236/jamp.2014.26054 Aerodynamic Optimization of
More informationImpact of numerical method on auto-ignition in a temporally evolving mixing layer at various initial conditions
Journal of Physics: Conference Series PAPER OPEN ACCESS Impact of numerical method on auto-ignition in a temporally evolving mixing layer at various initial conditions To cite this article: A Rosiak and
More informationNear-wall Reynolds stress modelling for RANS and hybrid RANS/LES methods
Platzhalter für Bild, Bild auf Titelfolie hinter das Logo einsetzen Near-wall Reynolds stress modelling for RANS and hybrid RANS/LES methods Axel Probst (now at: C 2 A 2 S 2 E, DLR Göttingen) René Cécora,
More informationDIRECT NUMERICAL SIMULATIONS OF HIGH SPEED FLOW OVER CAVITY. Abstract
3 rd AFOSR International Conference on DNS/LES (TAICDL), August 5-9 th, 2001, Arlington, Texas. DIRECT NUMERICAL SIMULATIONS OF HIGH SPEED FLOW OVER CAVITY A. HAMED, D. BASU, A. MOHAMED AND K. DAS Department
More informationDIRECT NUMERICAL SIMULATION OF SPATIALLY DEVELOPING TURBULENT BOUNDARY LAYER FOR SKIN FRICTION DRAG REDUCTION BY WALL SURFACE-HEATING OR COOLING
DIRECT NUMERICAL SIMULATION OF SPATIALLY DEVELOPING TURBULENT BOUNDARY LAYER FOR SKIN FRICTION DRAG REDUCTION BY WALL SURFACE-HEATING OR COOLING Yukinori Kametani Department of mechanical engineering Keio
More informationIntroduction of compressible turbulence
Introduction of compressible turbulence 1 Main topics Derive averaged equations for compressible turbulence Introduce a math. technique to perform averaging in presence of density variation Favre average
More informationBOUNDARY LAYER FLOWS HINCHEY
BOUNDARY LAYER FLOWS HINCHEY BOUNDARY LAYER PHENOMENA When a body moves through a viscous fluid, the fluid at its surface moves with it. It does not slip over the surface. When a body moves at high speed,
More informationSTUDY OF THE SECONDARY FLOW STRUCTURES CAUSED THE ADDITION FORWARD FACING STEP TURBULENCE GENERATED
Advances and Applications in Fluid Mechanics 2015 Pushpa Publishing House, Allahabad, India Published Online: May 2015 http://dx.doi.org/10.17654/aafmjul2015_129_144 Volume 18, Number 1, 2015, Pages 129-144
More informationNovel uses of DNS with turbulent separation for RANS models
Novel uses of DNS with turbulent separation for RANS models Gary Coleman*, Chris Rumsey* and Philippe Spalart** *NASA Langley Research Center **Boeing Commercial Airplanes 1 Outline q Flow: spatial separation
More informationNumerical investigation of nanosecond pulsed plasma actuators for control of shock-wave/boundary-layer separation
Numerical investigation of nanosecond pulsed plasma actuators for control of shock-wave/boundary-layer separation Kiyoshi Kinefuchi, 1,a) Andrey Y. Starikovskiy 2) and Richard B. Miles 2) 1 Research and
More informationMeysam ATASHAFROOZ, Seyyed Abdolreza GANDJALIKHAN NASSAB, and Amir Babak ANSARI
THERMAL SCIENCE: Year 014, Vol. 18, No., pp. 479-49 479 NUMERICAL INVESTIGATION OF ENTROPY GENERATION IN LAMINAR FORCED CONVECTION FLOW OVER INCLINED BACKWARD AND FORWARD FACING STEPS IN A DUCT UNDER BLEEDING
More informationThe mean velocity profile in the smooth wall turbulent boundary layer : 1) viscous sublayer
The mean velocity profile in the smooth wall turbulent boundary layer : 1) viscous sublayer u = τ 0 y μ τ = μ du dy the velocity varies linearly, as a Couette flow (moving upper wall). Thus, the shear
More informationThe role of coherent structures in subgrid-scale energy transfer within the log layer of wall turbulence
PHYSICS OF FLUIDS 18, 065104 2006 The role of coherent structures in subgrid-scale energy transfer within the log layer of wall turbulence V. K. Natrajan and K. T. Christensen a Department of Theoretical
More informationBoundary-Layer Theory
Hermann Schlichting Klaus Gersten Boundary-Layer Theory With contributions from Egon Krause and Herbert Oertel Jr. Translated by Katherine Mayes 8th Revised and Enlarged Edition With 287 Figures and 22
More informationEVALUATION OF SLUDGE REMOVAL CAPABILITIES FOR ADMP MIXER IN TANK 18
WSRC-TR-2003-00166 KEYWORDS: Sludge Suspension Computational Approach Sludge Mixing Jet Flow Model Mixing Pump Model RETENTION - Permanent EVALUATION OF SLUDGE REMOVAL CAPABILITIES FOR ADMP MIXER IN TANK
More informationWALL PRESSURE FLUCTUATIONS IN A TURBULENT BOUNDARY LAYER AFTER BLOWING OR SUCTION
WALL PRESSURE FLUCTUATIONS IN A TURBULENT BOUNDARY LAYER AFTER BLOWING OR SUCTION Joongnyon Kim, Kyoungyoun Kim, Hyung Jin Sung Department of Mechanical Engineering, Korea Advanced Institute of Science
More informationDirect numerical simulation of hypersonic turbulent boundary layers with varying freestream Mach number
48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition 4-7 January 2, Orlando, Florida AIAA 2-353 Direct numerical simulation of hypersonic turbulent boundary layers
More information