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  • 1
    Electronic Resource
    Electronic Resource
    Expression of the rice chloroplast psaA-psaB-rps14 gene cluster
    Amsterdam : Elsevier
    Plant Science 81 (1992), S. 93-102 
    Details
    ISSN: 0168-9452
    Keywords: P700 chlorophyll a protein ; plastid genes ; ribosomal protein S14 ; rice ; transcription
    Source: Elsevier Journal Backfiles on ScienceDirect 1907 - 2002
    Topics: Biology
    Type of Medium: Electronic Resource
    URL: http://linkinghub.elsevier.com/retrieve/pii/0168-9452(92)90028-K
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    Paper (German National Licenses)
    Fulltext
  • 2
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    β-Arrestins promote podocyte injury by inhibition of autophagy in diabetic nephropathy (2016)
    Springer Nature
    Details
    Publication Date: 2016-04-08
    Description: β-Arrestins promote podocyte injury by inhibition of autophagy in diabetic nephropathy Cell Death and Disease 7, e2183 (April 2016). doi:10.1038/cddis.2016.89 Authors: J Liu, Q X Li, X J Wang, C Zhang, Y Q Duan, Z Y Wang, Y Zhang, X Yu, N J Li, J P Sun & F Yi
    Electronic ISSN: 2041-4889
    Topics: Biology , Medicine
    Published by Springer Nature
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    PAPER CURRENT
  • 3
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    Grid generation for general three-dimensional configurations (1980)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: A suitable grid system for complex three dimensional configurations such as wing/body/nacelle shape for the solution of nonlinear transonic flow problems was constructed. Two approaches were explored based on Thompson's body fitted coordinate concept. The most general approach was to divide the computational domain into multiple rectangular blocks where the configuration itself was also represented by a set of blocks whose structure follows the natural lines of the configuration. The block structured grid system was adaptable to complex configurations and gives good grid quality near physical corners. However, it introduced algorithm issues for the flow solution concerning the treatment of nonanalytic grid block boundaries and nonstandard grid cells. These issues were explored in relation to the grid generation. A more limited approach treats a wing/body configuration with only a single rectangular block in computational space. The issues involving nonstandard cells were avoided, but other limitations on grid resolution appear. Both a linear and a nonlinear system of grid generation equations were developed including methods of grid control.
    Keywords: NUMERICAL ANALYSIS
    Type: NASA. Langley Research Center Numerical Grid Generation Tech.; p 355-366
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Application of boundary layer control to HSCT low speed configuration (1990)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: The feasibility of using boundary layer control (BLC) on a high speed civil transport (HSCT) high lift configuration for low speed performance improvement is studied. The possibility of using a part of the suction system previously designed for cruise laminar flow control (LFC) for low speed BLC mode was explored. A suction scheme for BLC was devised for the HSCT high lift configuration. The extent of the suction regions and levels were determined via panel method based inviscid flow analysis coupled with three-dimensional boundary layer analyses. The compatibility of the BLC suction requirements was assessed, and the modifications necessary to operate the system in both modes of operation, were determined. An assessment of the potential aerodynamic performance improvement resulting from an implementation of the BLC concept compared to an optimized simple flap configuration without BLC was made by an Euler code analysis of the simple flap configuration.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 90-3199
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Flow prediction for propfan engine installation effects on transport aircraft at transonic speeds (1986)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: An Euler-based method for aerodynamic analysis of turboprop transport aircraft at transonic speeds has been developed. In this method, inviscid Euler equations are solved over surface-fitted grids constructed about aircraft configurations. Propeller effects are simulated by specifying sources of momentum and energy on an actuator disc located in place of the propeller. A stripwise boundary layer procedure is included to account for the viscous effects. A preliminary version of an approach to embed the exhaust plume within the global Euler solution has also been developed for more accurate treatment of the exhaust flow. The resulting system of programs is capable of handling wing-body-nacelle-propeller configurations. The propeller disks may be tractors or pushers and may represent single or counterrotation propellers. Results from analyses of three test cases of interest (a wing alone, a wing-body-nacelle model, and a wing-nacelle-endplate model) are presented. A user's manual for executing the system of computer programs with formats of various input files, sample job decks, and sample input files is provided in appendices.
    Keywords: AERODYNAMICS
    Type: NASA-CR-3954 , NAS 1.26:3954
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Computational Simulations for Stability and Control: BCA State-of-the-Art (2004)
    In:  CASI
    Details
    Publication Date: 2018-06-11
    Description: The presentation will show some of our recent work in using the NASA-built Navier-Stokes solvers for various applications including airplane control surface effectiveness study, Reynolds number scaling, and high lift configuration analysis.
    Keywords: Computer Programming and Software
    Type: COMSAC: Computational Methods for Stability and Control, Part 2; 396-416; NASA/CP-2004-213028/PT2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Inviscid transonic flow computations with shock fitting (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: First-and second-order numerical procedures are presented for calculating two-dimensional transonic flows that treat shock waves as discontinuities. Their application to a simple but nontrivial problem for which there are limited theoretical results is discussed.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-145430
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Flow prediction for propfan configurations using Euler equations (1984)
    In:  Other Sources
    Details
    Publication Date: 2019-06-28
    Description: An Euler code has been developed for the analysis of a wing-mounted propfan configuration. Surface-fitted grids are used to represent the wing, fuselage, and nacelle geometry. The propeller is simulated by an actuator disk along a computational plane. A grid embedding technique is employed to capture detailed flow field resolution in the vicinity of the engine exhaust plume. Results of a NASA turboprop configuration are compared with test data. Specific issues on grid embedding and methods of resolving them are discussed.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 84-1645
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    A new method for designing shock-free transonic configurations (1978)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A method for the design of shock free supercritical airfoils, wings, and three dimensional configurations is described. Results illustrating the procedure in two and three dimensions are given. They include modifications to part of the upper surface of an NACA 64A410 airfoil that will maintain shock free flow over a range of Mach numbers for a fixed lift coefficient, and the modifications required on part of the upper surface of a swept wing with an NACA 64A410 root section to achieve shock free flow. While the results are given for inviscid flow, the same procedures can be employed iteratively with a boundary layer calculation in order to achieve shock free viscous designs. With a shock free pressure field the boundary layer calculation will be reliable and not complicated by the difficulties of shock wave boundary layer interaction.
    Keywords: AERODYNAMICS
    Type: NASA-CR-158063 , PAPER-78-114 , TED-78-04 , AIAA 11th Fluid and Plasma Dyn. Conf.; Jul 10, 1978 - Jul 12, 1978; Seattle, WA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 10
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    A new method for designing shock-free transonic configurations (1978)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A new method for the design of shock-free supercritical airfoils, wings, and three-dimensional configurations is described. Results illustrating this procedure in two and three dimensions are given. They include modifications to part of the upper surface of an NACA 64A410 airfoil that will maintain shock-free flow over a range of Mach numbers for a fixed lift coefficient, and the modifications required on part of the upper surface of a swept wing with an NACA 64A410 root section to achieve shock-free flow. While the results are given for inviscid flow, the same procedures can be employed iteratively with a boundary layer calculation in order to achieve shock-free viscous designs. With a shock-free pressure field the boundary layer calculation will be reliable and not complicated by the difficulties of shock-wave boundary-layer interaction.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 78-1114 , AD-A070888 , AFOSR-TR-79-0615 , Fluid and Plasma Dynamics Conference; Jul 10, 1978 - Jul 12, 1978; Seattle, WA
    Format: text
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    NASA TECHNICAL REPORTS
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