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  • 1
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    Sorption and Transport of Linear Esters and Branched Alkanes in Biaxially Oriented Poly(ethylene terephthalate) (2004)
    American Chemical Society
    Details
    Publication Date: 2004-06-01
    Print ISSN: 0888-5885
    Electronic ISSN: 1520-5045
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Published by American Chemical Society
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    PAPER CURRENT
  • 2
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    Characterization of Oxygen Scavenging Films Based on 1,4-Polybutadiene (2012)
    American Chemical Society
    Details
    Publication Date: 2012-05-21
    Print ISSN: 0888-5885
    Electronic ISSN: 1520-5045
    Topics: Chemistry and Pharmacology , Process Engineering, Biotechnology, Nutrition Technology
    Published by American Chemical Society
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    PAPER CURRENT
  • 3
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    Domain-decomposition algorithm applied to multielement airfoil grids (1992)
    In:  Other Sources
    Details
    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 30; 6, Ju; 1457-146
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    A multiblock grid generation technique applied to a jet engine configuration (1992)
    In:  CASI
    Details
    Publication Date: 2013-08-31
    Description: Techniques are presented for quickly finding a multiblock grid for a 2D geometrically complex domain from geometrical boundary data. An automated technique for determining a block decomposition of the domain is explained. Techniques for representing this domain decomposition and transforming it are also presented. Further, a linear optimization method may be used to solve the equations which determine grid dimensions within the block decomposition. These algorithms automate many stages in the domain decomposition and grid formation process and limit the need for human intervention and inputs. They are demonstrated for the meridional or throughflow geometry of a bladed jet engine configuration.
    Keywords: COMPUTER PROGRAMMING AND SOFTWARE
    Type: NASA. Langley Research Center, Software Surface Modeling and Grid Generation Steering Committee; p 477-485
    Format: application/pdf
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  • 5
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    Multiblock grid generation for jet engine configurations (1992)
    In:  CASI
    Details
    Publication Date: 2013-08-29
    Description: The goal was to create methods for generating grids with minimal human intervention that are applicable to a wide range of problems and compatible with existing numerical methods and with existing and proposed computers. The following topics that are related to multiblock grid generation are briefly covered in viewgraph form: finding a domain decomposition, dimensioning grids, grid smoothing, manipulating grids and decompositions, and some specializations for jet engine configurations.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Workshop on Grid Generation and Related Areas; p 79-84
    Format: text
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    NASA TECHNICAL REPORTS
  • 6
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    Space Transportation Propulsion Systems (2001)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: This report outlines the Space Transportation Propulsion Systems for the NPSS (Numerical Propulsion System Simulation) program. Topics include: 1) a review of Engine/Inlet Coupling Work; 2) Background/Organization of Space Transportation Initiative; 3) Synergy between High Performance Computing and Communications Program (HPCCP) and Advanced Space Transportation Program (ASTP); 4) Status of Space Transportation Effort, including planned deliverables for FY01-FY06, FY00 accomplishments (HPCCP Funded) and FY01 Major Milestones (HPCCP and ASTP); and 5) a review current technical efforts, including a review of the Rocket-Based Combined-Cycle (RBCC), Scope of Work, RBCC Concept Aerodynamic Analysis and RBCC Concept Multidisciplinary Analysis.
    Keywords: Aircraft Propulsion and Power
    Type: 2000 Numerical Propulsion System Simulation Review; 59-69; NASA/CP-2001-210673
    Format: application/pdf
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  • 7
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    A two-dimensional Euler solution for an unbladed jet engine configuration (1991)
    In:  Other Sources
    Details
    Publication Date: 2019-01-25
    Description: A two dimensional nonaxisymmetric Euler solution in a geometric representation of a jet engine configuration without blades is presented. The domain, including internal and external flow, is covered with a multiblock grid. To construct the grid, a domain decomposition technique is used to subdivide the domain and smooth grids are dimensioned and placed in each block. The grid contains 44 blocks which cover the external field, the inlet, bypass duct, core duct and nozzle of the nonaxisymmetric engine configuration. The geometry is symmetric about the meanline of the hub, but the grid is not since there is no symmetry condition applied to the grid between the two halves. With a symmetric grid at zero angle of attack, the measures of the solution would cancel exactly. With an asymmetric grid, the solution will not necessarily be symmetric and the lift coefficient will not necessarily be zero. Thus, grid asymmetry can be exploited to verify the resolution of the solution. The solution may be verified on the basis of five theoretical quantities: conservation of mass and energy, deviation of the lift coefficient from zero, deviation of the drag coefficient from zero, deviations from constant entropy, and deviations in the pressure distributions over the symmetric surfaces of the components. This technique is suitable for obtaining numerical solutions in complex geometries and provides a foundation for complete engine throughflow calculations.
    Keywords: AERODYNAMICS
    Type: CASI, Proceedings of the 3rd Canadian Symposium on Aerodynamics; p 186-193
    Format: text
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  • 8
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    Euler solutions for an unbladed jet engine configuration (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An Euler solution for an axisymmetric jet engine configuration without blade effects is presented. The Euler equations are solved on a multiblock grid which covers a domain including the inlet, bybass duct, core passage, nozzle, and the far field surrounding the engine. The simulation is verified by considering five theoretical properties of the solution. The solution demonstrates both multiblock grid generation techniques and a foundation for a full jet engine throughflow calculation.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA PAPER 92-0544
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    A Historical Review of Cermet Fuel Development and the Engine Performance Implications (2015)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: To better understand Cermet engine performance, examined historical material development reports two issues: High vaporization rate of UO2, High temperature chemical stability of UO2. Cladding and chemical stabilizers each result in large, order of magnitude improvements in high temperature performance. Few samples were tested above 2770 K. Results above 2770 K are ambiguous. Contemporary testing may clarify performance. Cermet sample testing during the NERVA Rover era. Important properties, melting temperature, vaporization rate, strength, Brittle-to-Ductile Transition, cermet sample test results, engine performance, location, peak temperature.
    Keywords: Propellants and Fuels; Spacecraft Propulsion and Power
    Type: GRC-E-DAA-TN21122 , Nuclear and Emerging Technologies for Space 2015; Feb 23, 2015 - Feb 26, 2015; Albuquerque, NM; United States
    Format: application/pdf
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  • 10
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    Pressurization of a Flightweight, Liquid Hydrogen Tank: Evaporation & Condensation at a Liquid/Vapor Interface (2017)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: This paper presents an analysis and simulation of evaporation and condensation at a motionless liquid/vapor interface. A 1-D model equation, emphasizing heat and mass transfer at the interface, is solved in two ways, and incorporated into a subgrid interface model within a CFD simulation. Simulation predictions are compared with experimental data from the CPST Engineering Design Unit tank, a cryogenic fluid management test tank in 1-g. The numerical challenge here is the physics of the liquid/vapor interface; pressurizing the ullage heats it by several degrees, and sets up an interfacial temperature gradient that transfers heat to the liquid phase-the rate limiting step of condensation is heat conducted through the liquid and vapor. This physics occurs in thin thermal layers O(1 mm) on either side of the interface which is resolved by the subgrid interface model. An accommodation coefficient of 1.0 is used in the simulations which is consistent with theory and measurements. This model is predictive of evaporation/condensation rates, that is, there is no parameter tuning.
    Keywords: Fluid Mechanics and Thermodynamics; Propellants and Fuels
    Type: GRC-E-DAA-TN43540 , AIAA Propulsion and Energy Forum and Exposition; Jul 10, 2017 - Jul 12, 2017; Atlanta, GA; United States
    Format: application/pdf
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