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  • 1
    Electronic Resource
    Electronic Resource
    Microstructural Comparison Between Melt Processed, In-situ Processed and Sintered Tl(Bi)-1223/Ag Tapes Using TEM. (1998)
    Springer
    Journal of superconductivity 11 (1998), S. 11-12 
    Details
    ISSN: 1572-9605
    Keywords: Tl-1223 ; microstructure ; TEM ; PIT ; processing
    Source: Springer Online Journal Archives 1860-2000
    Topics: Electrical Engineering, Measurement and Control Technology , Physics
    Notes: Abstract We have compared the microstructure of sintered, in-situ and melt processed Tl(Bi)-1223/Ag tapes using TEM. Melt processing of the tapes increases grain connectivity and removes amorphous phases leading to an improvement in the IC/B characteristics of the material. No long range grain alignment, which is the main requirement for improving the properties, was observed in the tapes.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1023/A:1022648905495
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    Paper (German National Licenses)
    Fulltext
  • 2
    Electronic Resource
    Electronic Resource
    Limitations To The Performance Of PIT Tl(Bi)-1223 Tapes (1998)
    Springer
    Journal of superconductivity 11 (1998), S. 103-106 
    Details
    ISSN: 1572-9605
    Keywords: Tl-1223 ; PIT tapes ; melt processing ; TEM ; bending
    Source: Springer Online Journal Archives 1860-2000
    Topics: Electrical Engineering, Measurement and Control Technology , Physics
    Notes: Abstract We have investigated the possibility of improving the weak link properties of Tl-1223 tape by melt processing, and also studied the technical limitations of coil fabrication using multimeter lengths of PIT tape. We conclude that melt processing does offer some potential for grain growth, but that grain alignment is only achieved in some places at the Ag/1223 interface. Until we can establish more control of the local grain alignment by altering the geometry of the samples, the properties of coils in high fields remains rather poor.
    Type of Medium: Electronic Resource
    URL: http://dx.doi.org/10.1023/A:1022610719124
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    Paper (German National Licenses)
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  • 3
    facet.materialart.
    Unknown
    A study of optimum cowl shapes and flow port locations for minimum drag with effective engine cooling, volume 2 (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The listings, user's instructions, sample inputs, and sample outputs of two computer programs which are especially useful in obtaining an approximate solution of the viscous flow over an arbitrary nonlifting three dimensional body are provided. The first program performs a potential flow solution by a well known panel method and readjusts this initial solution to account for the effects of the boundary layer displacement thickness, a nonuniform but unidirectional onset flow field, and the presence of air intakes and exhausts. The second program is effectually a geometry package which allows the user to change or refine the shape of a body to satisfy particular needs without a significant amount of human intervention. An effort to reduce the cruise drag of light aircraft through an analytical study of the contributions to the drag arising from the engine cowl shape and the foward fuselage area and also that resulting from the cooling air mass flowing through intake and exhaust sites on the nacelle is presented. The programs may be effectively used to determine the appropriate body modifications or flow port locations to reduce the cruise drag as well as to provide sufficient air flow for cooling the engine.
    Keywords: AERODYNAMICS
    Type: NASA-CR-159380 , NAS 1.26:159380
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
    facet.materialart.
    Unknown
    A study of optimum cowl shapes and flow port locations for minimum drag with effective engine cooling, volume 1 (1980)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: The contributions to the cruise drag of light aircraft arising from the shape of the engine cowl and the forward fuselage area and also that resulting from the cooling air mass flow through intake and exhaust sites on the nacelle were analyzed. The methods employed for the calculation of the potential flow about an arbitrary three dimensional body are described with modifications to include the effects of boundary layer displacement thickness, a nonuniform onset flow field (such as that due to a rotating propeller), and the presence of air intakes and exhausts. A simple, reliable, largely automated scheme to better define or change the shape of a body is also presented. A technique was developed which can yield physically acceptable skin friction and pressure drag coefficients for isolated light aircraft bodies. For test cases on a blunt nose Cessna 182 fuselage, the technique predicted drag reductions as much as 28.5% by body recontouring and proper placements and sizing of the cooling air intakes and exhausts.
    Keywords: AERODYNAMICS
    Type: NASA-CR-159379 , NAS 1.26:159379
    Format: application/pdf
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    NASA TECHNICAL REPORTS
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