National Institute of Aerospace
Computational Fluid Dynamics Seminar

A place to share ideas and problems for barrier-breaking developments

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▶ Contacts

Boris Diskin   [ E-mail ]
Hiroaki Nishikawa   [ E-mail ]
▶ Past Seminars

    Season 3 (2013-2014)
    Season 2 (2012-2013)
    Season 1 (2011-2012)

    List of Speakers
▶ NIA Researchers
Boris Diskin, Ph.D.  
Research Fellow, NIA
Research Associate Professor,
Mechanical and Aerospace Engineering,
University of Virginia

Adjoint-based optimization methods, Finite-volume discretizations, Multigrid methods on structured/unstructured grids
Web | E-mail
Yi Liu, Ph.D.  
Senior Research Scientist, NIA

high-order accurate methods, turbomachinery and rotorcraft applicaitons.
| E-mail
Hiroaki Nishikawa, Ph.D.  
Associate Research Fellow, NIA

Discretization and convergence acceleration methods for unstructured grids
Web | E-mail | CFD Notes                 View Hiroaki Nishikawa's LinkedIn profile Follow HiroNishikawa on Twitter
Matteo Parsani, Ph.D.  
Postdoctoral Fellow at NASA LaRC

high-order accurate methods for large-eddy simulation and aeroacoustics, efficient explicit and implicit time integrators and acceleration techniques for compressible flows
| E-mail
Sriram Rallabhandi, Ph.D.  
Sr. Research Engineer, NIA

Aircraft Design, Sonic Boom Modeling, Multi-Disciplinary Design Optimization, Aerodynamic Analysis, Computational Fluid Dynamics, Reduced Order Modeling and Model Order Reduction
Web | E-mail
Balaji Shankar Venkatachari, Ph.D.  
Postdoctoral Fellow, University of Alabama at Birmingham

Resident at the NASA Langley Research Center in the Computational AeroSciences Branch, working on numerical algorithm development, Hypersonics, TPS modeling (continuum and multi-scale modeling), and CAA.
▶ Faculties in Residence
Li-Shi Luo, Ph.D.  
The Richard F. Barry Jr. Distinguished Endowed Professor (in Residence, NIA)
Mathematics and Statistics,
Old Dominion University

Kinetic methods for CFD, Nonequilibrium flows, Complex fluids
Web | E-mail
Bill Moore, Ph.D.  
Professor in Residence, NIA
Atmospheric & Planetary Sciences,
Hampton University

Thermal Evolution of Planet and Satellite Inteiors, Dynamical Evolution of Planets and Satellites, Coupled Atmosphere-Interior Modeling of Planets, What Makes a Planetary Body Habitable?
Web | E-mail
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NIA CFD Seminar Schedule

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Click the camera icon below to go directly to the video for each seminar.

08-04-2015   11:00am - noon (EST)   NIA Room 137      video

M4D, an Open Source Research CFD Code for the Calculation of Classical and Turbulent/Transitional Flows

M4D features unsteady convection adapted control volumes and the MARV/MARVS Reynolds stress models. Convection adapted control volumes are a paradigm shift in CFD. Used with tri-linear discretization of convected properties in space over a fixed grid (formally 3-d 2nd-order accurate), they provide a balance between accuracy and stability not found in fixed volume methods. The MARV/MARVS Reynolds stress models are advanced turbulence models which calculate transition naturally based on an understanding of homogeneous shear flow at high dimensionless strain rates. The presentation will concentrate on the convection adapted control volumes - the method, the combination of stability and accuracy, with the examples of an inviscid Kelvin-Helmholtz shear layer instability and near-DNS of flow in a square channel. The steady flow Reynolds stress model examples of transitional flow and heat transfer in a turbine cascade (Butler et al.) and of a backward facing step (Kasagi) also use the convection adapted control volumes.

[ presentation file (pdf) ] Joan G. Moore

Speaker Bio: It is fifty years since Joan and John Moore met in M.I.T.'s Gas Turbine Laboratory. John had come with a B.Sc. (Eng.) in Mechanical Engineering from Imperial College, London to obtain an S.M. and then an Sc.D from M.I.T. Joan with a B.S. in Applied Mathematics from M.I.T., had the job of writing computer codes and helping Graduate students with theirs. Thus began a life-long CFD and turbulence modeling collaboration. John is currently a Professor Emeritus of Mechanical Engineering at Virginia Tech. Their first 'retirement' project, their book "Functional Reynolds Stress Modeling" was published in 2006. And now Joan has written her 4th CFD code, M4D, but her first one unfettered by external sponsorship.

Further details can be found at Homepage of Joan and John Moore .

Relevant Publications: Using Multi-Dimensional Linear Discretization Over Unsteady Convection Adapted Control Volumes, AIAA-2014-2780.
[ Paper (pdf) ]

[ Paper (pdf) ]

An RSM/EVM Flow/Heat Transfer Model Applied to Pre-Transitional and Turbulent Boundary Layers, AIAA -2010-4314,
[ Paper (pdf) ]

07-14-2015   1:00pm - 2:00pm (EST)   NIA Room 142      video

Flow Analysis and Adjoint-Based Design Optimization Using a High-Order CFD Method

The computational analysis and design for multiscale physics and complex systems demand computationally accurate and efficient discretization methods. High-order discretization methods have gained increasing popularity in a wide range of application scenarios in sciences and engineering. In this presentation, the focuses will be two-fold. First, the techniques of a highorder discontinuous Galerkin finite element method for aerodynamic turbulent flow simulation will be discussed. In particular, the spatial discretization procedures and the implementation for Reynolds Averaged Navier-Stokes as well as large-eddy simulation will be covered in detail. The second focus will be on the integration of the high-order CFD method with sensitivity analysis capabilities for aerodynamic shape optimization. The discrete adjoint method is derived in a mathematically rigorous framework and provides important search directions towards an optimum design solution. Simulation of turbulence using the developed high-order discontinuous Galerkin method will be presented with an emphasis on examining the accuracy of different orders of discretization schemes. Several optimization examples will be described as well to demonstrate the effectiveness of the discrete adjoint algorithm in steady and unsteady design optimization.

[ presentation file (pdf) ] Li Wang

Speaker Bio: Li Wang earned her PhD degree in Mechanical Engineering from the University of Wyoming in 2009 and she is currently a Research Assistant Professor in the SimCenter at the University of Tennessee, Chattanooga. She has successfully developed computational software to perform high-fidelity aerodynamic simulation and design. Her research centers on turbulent flow simulation and modeling, high-order finite element CFD methods, adjoint-based sensitivity analysis and design optimization, adaptive meshing, multigrid acceleration strategies, and highperformance computing. Since 2009 she has extended the software capabilities to high-frequency electromagnetic applications. She is currently serving as Associate Member of the American Institute of Aeronautics and Astronautics (AIAA) Applied Aerodynamics Technical Committee and has been an active participant in multiple research grants and contracts from NASA, DoD and U.S. Army.

01-29-2015   11:00am - noon (EST)   NIA Room 137      video

Towards Aerospace Design in the Age of Extreme-Scale Supercomputing

Extreme scale supercomputing will soon offer a million times the computing power of a desktop - an as drastic upgrade as that from a slide rule to a desktop computer in the 1990s. I believe this will revolutionize how we aerospace engineers work. It will enable us to rapidly and confidently refine and optimize our designs. But this revolution can only happen through innovating our computational algorithms. In Computational Fluid Dynamics, high-fidelity simulations such as Large Eddy Simulation can often reliably predict the performance of aerospace vehicles and engines. But with today's algorithms, these simulations take days if not weeks. With today's optimization algorithms, it may take months if not years for us to reach a good design. Can we shorten each high fidelity CFD simulation to minutes, by innovating how we solve PDEs, better utilizing the skyrocketing concurrency in supercomputers? Better, can we shorten an entire high fidelity optimization to minutes by innovating how we do optimization, again utilizing more concurrency than we currently can? Even better, can we shorten a high fidelity optimization with hundreds of design parameters to minutes, by computing high fidelity design gradients, even when the simulations are turbulent and chaotic, and gradients in the traditional sense would diverge? I believe that the answers are yes, yes and yes. In this talk, I will show you why I believe so, and discuss how we all can advance aerospace design into the age of extreme-scale supercomputing.

[ presentation file (pdf) ] Qiqi Wang

Speaker Bio: Qiqi Wang is an assistant professor of aeronautics and astronautics at MIT. He obtained his PhD from Stanford in 2009, and B.S. from University of Science and Technology of China in 2004.

12-16-2014   11:00am - noon (EST)   NIA Room 137      video

Accuracy-Preserving Boundary Quadrature for Edge-Based Finite-Volume Scheme: Third-order accuracy without curved elements

This talk will discuss a third-order edge-based finite-volume scheme on unstructured grids. It will be shown why the edge-based scheme can be third-order and also why it cannot be third-order if the numerical flux is exact for quadratic fluxes. A general boundary flux quadrature formula is presented that preserves third-order accuracy at boundary nodes with linear elements. Numerical results show that the general formula as well as acccurate boundary normals are essential to achieve third-order accuracy for a curved boundary problem with linear elements.

[ presentation file (pdf) ] Hiro Nishikawa

Speaker Bio: Dr. Hiro Nishikawa is Associate Research Fellow, NIA. He earned Ph.D. in Aerospace Engineering and Scientific Computing at the University of Michigan in 2001. He then worked as a postdoctoral fellow at the University of Michigan on adaptive grid methods, local preconditioning methods, multigrid methods, rotated-hybrid Riemann solvers, high-order upwind and viscous schemes, etc., and joined NIA in 2007. His area of expertise is the algorithm development for CFD, focusing on hyperbolic methods for robust, efficient, highly accurate viscous discretization schemes.

[ Homepage | CFD book | Free CFD codes | CFD Notes ]

Relevant Publication: H. Nishikawa, " Accuracy-preserving boundary flux quadrature for finite-volume discretization on unstructured grids", Journal of Computational Physics, Volume 281, January 2015, Pages 518-555, 2015.
[ bib | pdf | journal ]

First, Second, and Third-Order Finite-Volume Schemes for Navier-Stokes Equations, AIAA Paper, 2014-2091. [ AIAA Paper 2014-2091 (pdf) ]

12-02-2014   11:00am - Noon (EST)   NIA Room 137      webcast

Entropy stable wall boundary conditions for the compressible Navier-Stokes equations

Non-linear entropy stability and a summation-by-parts framework are used to derive entropy stable wall boundary conditions for the compressible Navier-Stokes equations. A semi- discrete entropy estimate for the entire domain is achieved when the new boundary condi- tions are coupled with an entropy stable discrete interior operator. The data at the boundary are weakly imposed using a penalty flux approach and a simultaneous-approximation-term penalty technique. Although discontinuous spectral collocation operators are used herein for the purpose of demonstrating their robustness and efficacy, the new boundary conditions are compatible with any diagonal norm summation-by-parts spatial operator, including fi- nite element, finite volume, finite difference, discontinuous Galerkin, and flux reconstruction schemes. The proposed boundary treatment is tested for three-dimensional subsonic and supersonic flows. The numerical computations corroborate the non-linear stability (entropy stability) and accuracy of the boundary conditions.

[ presentation file (pdf) ] Matteo Parsani

Speaker Bio: Dr. Matteo Parsani is currently a Post-doctoral Fellow at NASA Langley Research Center, working with Dr. Mark H. Carpenter. Prior to this he was a Post-doctoral Researcher at KAUST, working in the group of Professor David Ketcheson. He received his Ph.D. in Mechanical and Aerospace Engineering from Free University of Brussels in December 2010. His research interests include high-order accurate methods for large-eddy simulation and aeroacoustics, efficient explicit and implicit time integrators and acceleration techniques for compressible flows. In 2011 his PhD thesis was selected among the best National Ph.D. theses to be presented at the ECCOMAS Olympiad workshop in Athens.

Relevant Publication: Matteo Parsani, Mark H. Carpenter, and Eric J. Nielsen, Entropy Stable Wall Boundary Conditions for the Compressible Navier-Stokes Equations, NASA-TM--2014-218282. [ NASA-TM--2014-218282 (pdf) ]

10-06-2014   1:00pm - 2:00pm (EDT)   NIA Room 101      video not available (realtime webcast only)

Recent Applications of Overset Mesh Technology in SC/Tetra

Software Cradle has introduced overset mesh technology to SC/Tetra since 2007, and we are dealing with a lot of demands from industries using the technology. This is a necessary function for flow simulation with moving components in complex geometries, which is not uncommon in real products. SC/Tetra's overset technology has been improved continuously, and is now able to be coupled with free-surface analysis, flow-structure interaction and dynamical moving components (6DOF). In the latest version, a special treatment for analyses of the flow in piston engines was introduced. The treatment achieves practical accuracy for mass conservation in the cylinder.

[ presentation file (pdf) ] Tomohiro Irie

Speaker Bio: Tomohiro Irie is Assistant Manager of Software Engineering Department at Software Cradle Co., Ltd. in charge of SC/Tetra's solver component.

09-09-2014   11:00am - noon (EDT)   NIA Room 137      video

Numerical Simulations of General Conservation Laws Using the Space-Time Conservative CESE Method

Governing equations of most engineering disciplines can be written as general conservation laws by enforcing mass, momentum, and energy balances. Modern computational methods are devised to provide accurate solutions to these conservation laws in the discretized space. The space-time conservation element solution element (CESE) method introduced in 1990s is a numerical framework for general conservation laws designed to provide discretized solutions in the space-time domain with considerations to ensure accuracy and robustness. The CESE method is constructed based on a non-dissipative, space time inversion invariant core scheme. Numerical dissipations are added as required. Discretized equations for dependent variables and high derivatives are formulated by enforcing both local and global conservations. It can be shown that fundamental quantities such as mass, momentum, and energy are strictly conserved both in the local conservation elements as well as the entire computational domain. To handle solutions with discontinuities, the integration volumes have interfaces that only encompass the smooth regions where solution polynomials are valid. With these constructs, the CESE numerical framework is free of ad-hoc reconstructions of physical quantities associated with interfacial discontinuity or approximations of kinetic energy. This talk discusses the fundamental concepts and development of the CESE framework with primary focus on 3D Navier-Stokes computations. High fidelity simulations of problems with multiple temporal/spatial-scales and physics are tackled with time accurate local time-stepping and high-order frameworks for unstructured meshes. Applications of the CESE method in other disciplines outside of NASA will be briefly discussed.

[ presentation file (pdf) ] Chau-Lyan Chang

Speaker Bio: Dr. Chau-Lyan Chang is a research scientist from the Computational AeroSciences Branch at NASA Langley Research Center. His primary research interest is in unstructured mesh CFD methods and code development. He also works on numerical computations of boundary layer stability and transitions. He actively maintains LASTRAC software and interacts with users from academia and industry. .

08-27-2014   11:00am - noon (EDT)   NIA Room 101      video

Structural and Multidisciplinary Design Optimization of Aircraft with Next-Generation Lightweight Materials

The use of advanced lightweight structures has enabled significant performance improvements for the present generation of transport aircraft. New structural materials, manufacturing techniques and multi-functional structural technologies will lead to even greater improvements for future aircraft. These new technologies give engineers greater flexibility to tailor aircraft structures to meet stringent design requirements. However, the large design space associated with this flexibility can be difficult to navigate since there is a limited knowledge base to help guide design decisions. Advanced computational design methods that employ high-fidelity structural and multidisciplinary analysis are key tools to help engineers understand the complex trade-offs inherent in aircraft design, especially in the context of advanced structural technologies. In this seminar, I will present our work on structural and aerostructural optimization that begins to address these challenges. To meet the computational demands of high-fidelity simulation and design, we use gradient-based design optimization techniques in conjunction with parallel computational methods and efficient adjoint-based derivative evaluation. To illustrate our efforts in these areas, I will describe the development of our in-house parallel finite-element code designed for multidisciplinary analysis and gradient-based optimization of composite structures called the Toolkit for the Analysis of Composite Structures (TACS). To demonstrate the capabilities of our structural and aerostructural design optimization framework, I will present the results of a study comparing the design of metallic and composite wings for a large transport aircraft. These results will show the benefits of using an integrated, gradient-based aerostructural analysis and design optimization framework.

[ presentation file (pdf) ] Graeme Kennedy

Speaker Bio: Dr. Graeme Kennedy is an Assistant Professor in the School of Aerospace Engineering at the Georgia Institute of Technology where he leads his research group focused on developing novel design optimization methods for structural and multidisciplinary aerospace systems. Before joining the Georgia Tech faculty, he worked as a Postdoctoral Research Fellow at the University of Michigan in the Multidisciplinary Design Optimization lab. He received his Ph.D. from the University of Toronto Institute for Aerospace Studies (UTIAS) under the supervision of Prof. Joaquim R.R.A. Martins in 2012 and hisM.A.Sc. from UTIAS under the supervision of Prof. Jorn Hansen in 2007. He received his undergraduate degree in Aerospace Engineering from the University of Toronto in 2005. A complete list of papers and ongoing projects is available on Dr. Kennedy's website:

08-26-2014   11:00am - noon (EDT)   NIA Room 137      video

First-, Second-, and Third-Order Hyperbolic Navier-Stokes Solver

Is it possible that a third-order CFD solver is less expensive on a given grid than a conventional second-order solver? No, it is impossible because a higher-order scheme requires more work on the same grid. However, as history demonstrates, it only takes a radical idea to turn the impossible into the possible. This talk will investigate whether the hyperbolization of the viscous terms is radical enough to make it happen. The Navier-Stokes equations are made hyperbolic, discretized by first, second, and third-order finite-volume schemes with upwind fluxes, and solved by a fully implicit solver: Newton's method for the first-order scheme, and a defect correction method for others. The developed solver will be compared with a conventional second-order solver for some simple but realistic viscous flow problems, focusing on computation time and accuracy especially in the viscous stresses and heat fluxes on fully unstructured viscous grids.

[ presentation file (pdf) ] Hiro Nishikawa

Speaker Bio: Dr. Hiro Nishikawa is Associate Research Fellow, NIA. He earned Ph.D. in Aerospace Engineering and Scientific Computing at the University of Michigan in 2001. He then worked as a postdoctoral fellow at the University of Michigan on adaptive grid methods, local preconditioning methods, multigrid methods, rotated-hybrid Riemann solvers, high-order upwind and viscous schemes, etc., and joined NIA in 2007. His area of expertise is the algorithm development for CFD, focusing on hyperbolic methods for robust, efficient, highly accurate viscous discretization schemes.

[ Homepage | CFD book | Free CFD codes | CFD Notes ]

Relevant Publications: First, Second, and Third-Order Finite-Volume Schemes for Navier-Stokes Equations, AIAA Paper, 2014-2091. [ AIAA Paper 2014-2091 (pdf) ]

First, Second, and Third-Order Finite-Volume Schemes for Advection-Diffusion, JCP, Volume 273, 2014. [ Preprint (pdf) | Journal ]

First, Second, and Third-Order Finite-Volume Schemes for Diffusion, JCP, Volume 256, 2014 [ Preprint (pdf) | Journal ]

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