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52nd AIAA Aerospace Sciences Meeting - AIAA Science and Technology Forum and Exposition, SciTech 2014

作者： Sozer, Emre Brehm, Christoph Kiris, Cetin C. Science and Technology Corporation Moffett Field CA 94035 United States NASA Ames Research Center Applied Modeling and Simulation Branch NAS Division MS N258-2 Moffett Field CA 94035 United States

ISBN: (数字)9781624102561

ISBN: (纸本)9781624102561

A survey of gradient reconstruction methods for cell-centered data on unstructured meshes is conducted within the scope of accuracy assessment. Formal order of accuracy, as well as error magnitudes for each of the studied methods, are evaluated on a complex mesh of various cell types through consecutive local scaling of an analytical test function. The tests highlighted several gradient operator choices that can consistently achieve 1st order accuracy regardless of cell type and shape. The tests further offered error comparisons for given cell types, leading to the observation that the 'ideal' gradient operator choice is not universal. Practical implications of the results are explored via CFD solutions of a 2D inviscid standing vortex, portraying the discretization error properties. A relatively naive, yet largely unexplored, approach of local curvilinear stencil transformation exhibited surprisingly favorable properties.

关键词： Cells

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Computational assessment of the boundary layer ingesting nacelle design of the D8 aircraft 52

Computational assessment of the boundary layer ingesting nac...

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52nd AIAA Aerospace Sciences Meeting - AIAA Science and Technology Forum and Exposition, SciTech 2014

作者： Pandya, Shishir A. Huang, Arthur Espitia, Alejandro Uranga, Alejandra NASA Ames Research Center Applied Modeling and Simulation Branch NAS Division Mail Stop 258-2 Moffett Field CA United States Massachusetts Institute of Technology Dept. of Aeronautics and Astronautics Cambridge MA United States

ISBN: (数字)9781624102561

ISBN: (纸本)9781624102561

The benefit of boundary layer ingestion (BLI) is computed for the D8 aircraft, a nextgeneration subsonic transport concept. Solutions from Overflow, a viscous overset RANS CFD solver with an actuator-disk propulsor model, are used for the analysis. Computational results from an unpowered version of the aircraft are validated against a wind tunnel experiment, followed by a comparison of the performance of two D8 configurations: one with conventional, non-BLI propulsors, and another with BLI propulsors. The BLI configuration is shown to require 9% less propulsor power relative to the conventional configuration at the simulated cruise condition. It is shown that the difference is due to reduced entropy generation, associated with wake and jet mixing in the BLI configuration.

关键词： Aerodynamics

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Specialized CFD grid generation methods for near-field sonic boom prediction 52

Specialized CFD grid generation methods for near-field sonic...

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52nd AIAA Aerospace Sciences Meeting - AIAA Science and Technology Forum and Exposition, SciTech 2014

作者： Park, Michael A. Campbell, Richard L. Elmiliguiz, Alaa Cliff, Susan E. Nayani, Sudheer N. NASA Langley Research Center Computational AeroSciences Branch Hampton VA 23681 United States NASA Ames Research Center Configuration Aerodynamics Branch Moffett Field CA 94035 United States Analytical Services and Materials Inc Applied Modeling and Simulation Branch Hampton VA 23666 United States

ISBN: (数字)9781624102561

ISBN: (纸本)9781624102561

Ongoing interest in analysis and design of low sonic boom supersonic transports re-quires accurate and effcient Computational Fluid Dynamics (CFD) tools. Specialized grid generation techniques are employed to predict near-field acoustic signatures of these configurations. A fundamental examination of grid properties is performed including grid alignment with ow characteristics and element type. The issues affecting the robustness of cylindrical surface extrusion are illustrated. This study will compare three methods in the extrusion family of grid generation methods that produce grids aligned with the freestream Mach angle. These methods are applied to configurations from the First AIAA Sonic Boom Prediction Workshop.

关键词： Computational fluid dynamics

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26th Annual Computational Neuroscience Meeting (CNS*2017) of the Organization for Computational Neuroscience Antwerp, Belgium, July 15-20, 2017

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BMC NEUROSCIENCE 2017年第SUPPL 1期18卷 59-59页

作者： [Anonymous] Indiana University Purdue University Indianapolis Indianapolis IN 46032 USA Stark Neurosciences Research Institute Indiana University School of Medicine Indianapolis IN 46032 USA Department of Mathematics East Carolina University Greenville NC 27858 USA Jülich Supercomputing Centre Forschungszentrum Jülich 52425 Jülich Germany Future Systems Swiss National Supercomputing Centre 8092 Zurich Switzerland User Engagement and Support Swiss National Supercomputing Centre 6900 Lugano Switzerland Institut de Neurosciences des Systèmes Aix Marseille Univ 13005 Marseille France Simulation Lab Neuroscience Forschungszentrum Jülich Jülich Germany Department of Experimental Psychology Ghent University 9000 Ghent Belgium Donders Center for Cognitive Neuroimaging Radboud University 6525HR Nijmegen The Netherlands Department of Electrical Computer and Energy Engineering University of Colorado Boulder CO 80309 USA Department of Neurosurgery Johns Hopkins School of Medicine Baltimore MD 21287 USA Department of Neurology Johns Hopkins School of Medicine Baltimore MD 21287 USA Department of Otolaryngology Johns Hopkins School of Medicine Baltimore MD 21287 USA INSERM U968 Paris France Sorbonne Universités UPMC University Paris 06 UMR_S 968 Institut de la Vision Paris France CNRS UMR_7210 Paris France Department of Computer Architecture and Technology University of Granada (CITIC) Granada Spain Sorbonne Universités UPMC Univ Paris 06 INSERM CNRS Institut de la Vision Paris France Department of Adaptive Machine Systems Osaka University Osaka Japan Department of Computer Science University of Cergy-Pontoise Cergy-Pontoise France Department of Physics and Astronomy College of Charleston Charleston SC 29424 USA School of Physics Faculty of Science University of Sydney Sydney NSW 2006 Australia Center of Excellence for Integrative Brain Function Australian Research Council Sydney Australia Max Planck Institute for Human Cognitive and Brain Sciences Saxony Lei

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An overview of the characterization of the space launch system aerodynamic environments

An overview of the characterization of the space launch syst...

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52nd AIAA Aerospace Sciences Meeting - AIAA Science and Technology Forum and Exposition, SciTech 2014

作者： Blevins, John A. Campbell Jr., John R. Bennett, David W. Rausch, Russ D. Gomez, Reynaldo J. Kiris, Cetin C. NASA Marshall Space Flight Center Aerosciences Branch Huntsville AL 35812 United States NASA Langley Research Center Vehicle Analysis Branch Vehicle Analysis Branch Hampton VA 23681 United States NASA Johnson Space Center Applied Aeroscience and CFD Branch Houston TX 77058 United States NASA Ames Research Center Applied Modeling and Simulation Branch Moffett Field CA 94035 United States

ISBN: (纸本)9781624102561

Aerodynamic environments are some of the first engineering data products that are needed to design a space launch vehicle. These products are used in performance predic- tions, vehicle control algorithm design, as well as determing loads on primary and secondary structures in multiple discipline areas. When the National Aeronautics and Space Admin- istration (NASA) Space Launch System (SLS) Program was established with the goal of designing a new, heavy-lift launch vehicle first capable of lifting the Orion Program Multi- Purpose Crew Vehicle (MPCV) to low-earth orbit and preserving the potential to evolve the design to a 130 metric ton cargo launcher, the data needs were no different. Upon commencement of the new program, a characterization of aerodynamic environments were immediately initiated. In the time since, the SLS Aerodynamics Team has produced data describing the majority of the aerodynamic environment definitions needed for structural design and vehicle control under nominal fiight conditions. This paper provides an overview of select SLS aerodynamic environments completed to date.

关键词： NASA

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26th Annual Computational Neuroscience Meeting (CNS*2017): Part 3 Antwerp, Belgium. 15-20 July 2017 Abstracts

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BMC NEUROSCIENCE 2017年第SUPPL 1期18卷 95-176页

作者： [Anonymous] Department of Neuroscience Yale University New Haven CT 06520 USA Department Physiology & Pharmacology SUNY Downstate Brooklyn NY 11203 USA NYU School of Engineering 6 MetroTech Center Brooklyn NY 11201 USA Departament de Matemàtica Aplicada Universitat Politècnica de Catalunya Barcelona 08028 Spain Institut de Neurobiologie de la Méditerrannée (INMED) INSERM UMR901 Aix-Marseille Univ Marseille France Center of Neural Science New York University New York NY USA Aix-Marseille Univ INSERM INS Inst Neurosci Syst Marseille France Laboratoire de Physique Théorique et Modélisation CNRS UMR 8089 Université de Cergy-Pontoise 95300 Cergy-Pontoise Cedex France Department of Mathematics and Computer Science ENSAT Abdelmalek Essaadi’s University Tangier Morocco Laboratory of Natural Computation Department of Information and Electrical Engineering and Applied Mathematics University of Salerno 84084 Fisciano SA Italy Department of Medicine University of Salerno 84083 Lancusi SA Italy Dipartimento di Fisica Università degli Studi Aldo Moro Bari and INFN Sezione Di Bari Italy Data Analysis Department Ghent University Ghent Belgium Coma Science Group University of Liège Liège Belgium Cruces Hospital and Ikerbasque Research Center Bilbao Spain BIOtech Department of Industrial Engineering University of Trento and IRCS-PAT FBK 38010 Trento Italy Department of Data Analysis Ghent University Ghent 9000 Belgium The Wellcome Trust Centre for Neuroimaging University College London London WC1N 3BG UK Department of Electronic Engineering NED University of Engineering and Technology Karachi Pakistan Blue Brain Project École Polytechnique Fédérale de Lausanne Lausanne Switzerland Departement of Mathematics Swansea University Swansea Wales UK Laboratory for Topology and Neuroscience at the Brain Mind Institute École polytechnique fédérale de Lausanne Lausanne Switzerland Institute of Mathematics University of Aberdeen Aberdeen Scotland UK Department of Integrativ

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Qualitative modeling and analysis of the indoleamine 2,3-dioxygenase regulatory network in homeostasis and disease

Qualitative modeling and analysis of the indoleamine 2,3-dio...

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International Conference on Fuzzy Systems and Knowledge Discovery (FSKD)

作者： Kashif Asghar Jamil Ahmed Javaria Ashraf Amjad Ali Hussnain Ahmed Janjua Sheeba Murad Atta-ur-Rehman School of Applied Biosciences National University of Science & Technology (NUST) Islamabad Pakistan Research Center for Modeling & Simulation National University of Science & Technology(NUST) Islamabad Pakistan

ISBN: (纸本)9781479951499

Indoleamine 2,3-dioxygenase (IDO) has key role in immune regulation and it acts as a constituent of the inflammatory reaction allied with infection, allergic diseases, autoimmunity and cancer. IDO function as an immunosuppressive enzyme, which degrades the tryptophan into kynurenine and other downstream metabolites. Interferon gamma (IFN-γ) is a potent inducer of IDO. Transforming growth factor-beta (TGF-β) is the negative regulator of IDO. Both the TGF-β and IFN-γ have opposite effects on various cellular functions. IFN-γ and TGF-β inhibit the activity of each other through different pathways. In the pathological state when the homeostasis disturb, the impairment of IDO provides significant role in the pathogenesis of disease. The modeling of the Gene regulatory network (GRN) of IDO, IFN-γ and TGF-β using of René Thomas Formalism, help us in understanding their dynamical behaviors. We observe two types of steady states behaviors in this study. The cycle shows the homeostasis of IDO and TGF-β while IFN-γ is inactive (silent). The stable state shows the high expression levels of IFN-γ and IDO while TGF-β is silent. These findings recognized prospective novel targets for therapy in a range of clinical conditions, including, inflammation, tumor resistance and autoimmunity.

关键词： Immune system Cancer Tumors Diseases Steady-state Analytical models

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Assessing the purity of CNT from its composite with polymer - A new approach

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AIP Conference Proceedings 2014年第1期1591卷 534-536页

作者： J. C. Maurya Soumen Karmakar Sukratu Barve S. V. Bhoraskar A. K. Das V. L. Mathe Department of Physics University of Pune Pune- 411007 India Department of Applied Physics Birla Institute of Technology Mesra Deoghar Campus-835215 India Centre for Modeling and Simulation University of Pune Pune -411007 India Laser and Plasma Technology Division Bhabha Atomic Research Centre Trombay Mumbai- 400085 India

This study focuses on calculating the electrical properties of composites of CNTs with polystyrene within the framework of percolation theory. Nano-composites, with multiwall carbon nanotubes (MWCNTs) as a filler; especially synthesized in a dc arc plasma system in presence of focusing electric field, have been shown to exhibit metallic behavior. The purity of the MWCNTs prepared under the optimized focusing voltage of 400 V is then seen to be much higher as compared to the one synthesized at zero focusing voltage.

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Verification and validation studies for the LAVA CFD solver

Verification and validation studies for the LAVA CFD solver

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21st AIAA Computational Fluid Dynamics Conference

作者： Moini-Yekta, Shayan Barad, Michael F. Sozer, Emre Brehm, Christoph Housman, Jeffrey A. Kiris, Cetin C. Applied Modeling and Simulation Branch NASA Ames Research Center Moffett Field CA 94035 United States Applied Modeling and Simulation Branch Science and Technology Corporation Moffett Field CA 94035 United States Mechanical and Aeronautical Engineering University of California Davis United States

Verification and validation studies applied to the Launch Ascent and Vehicle Aerodynamics (LAVA) computational fluid dynamics (CFD) solver is presented. A modern strategy for verification and validation is implemented incorporating verification tests, validation benchmarks, continuous integration and version control methods for automated testing in a collaborative development environment. The purpose of the approach is to integrate the verification and validation process into the development of the solver and improve productivity. The procedure uses the Method of Manufactured Solutions (MMS) for the verification of 2D Euler equations and 3D Navier-Stokes equations. A method for systematic refinement of unstructured grids is also presented. Inviscid vortex propagation and flow over a flat plate are included in the verification study. simulation results using laminar and turbulent flow past a NACA 0012 airfoil and ONERA M6 wing are validated against experimental data compare to existing numerical results.

关键词： Computational fluid dynamics

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Summary of the 2008 NASA fundamental aeronautics program sonic boom prediction workshop 51

Summary of the 2008 NASA fundamental aeronautics program son...

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51st AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2013

作者： Park, Michael A. Aftosmis, Michael J. Campbell, Richard L. Carter, Melissa B. Cliff, Susan E. Bangert, Linda S. NASA Langley Research Center Computational AeroSciences Branch Configuration Aerodynamics Branch Hampton VA 23681 United States NASA Ames Research Center Modeling and Simulation Branch Moffett Field CA 94035 United States NASA Ames Research Center Applied Modeling and Simulation Branch Moffett Field CA 94035 United States

ISBN: (数字)9781624101816

ISBN: (纸本)9781624101816

The Supersonics Project of the NASA Fundamental Aeronautics Program organized an internal sonic boom workshop to evaluate nearfield sonic boom prediction capability at the Fundamental Aeronautics Annual Meeting in Atlanta, Georgia on October 8, 2008. Workshop participants computed sonic boom signatures for three non-lifting bodies and two lifting configurations. A cone-cylinder, parabolic, and quartic bodies of revolution comprised the non-lifting cases. The lifting configurations were a simple 69-degree delta wing body and a complete low-boom transport configuration designed during the High Speed research Project in the 1990s with wing, body, tail, nacelle, and boundary layer diverter components. The AIRPLANE, Cart3D, FUN3D, and USM3D flow solvers were employed with the ANET signature propagation tool, output-based adaptation, and a priori adaptation based on freestream Mach number and angle of attack. Results were presented orally at the workshop. This article documents the workshop, results, and provides context on previously available and recently developed methods.

关键词： NASA

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