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  • NONMETALLIC MATERIALS  (2)
  • AIRCRAFT PROPULSION AND POWER  (1)
  • 1975-1979  (3)
  • 1
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    Unknown
    Evaluation of a low-density polyimide foam in a dynamic, high temperature environment (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A low density polyimide foam material was tested in an arc tunnel to determine its potential for heat shield application on aerospace vehicles. The results show that the material has some reuse potential at surface temperatures as high as 750 K. When a black refractory paint was applied to the surface of the material, the surface recession was negligible at 750 K. An analytical thermal conductivity was derived for this material which, combined with measured thermal property values, can be used to make preliminary design thickness calculations for heat shield applications.
    Keywords: NONMETALLIC MATERIALS
    Type: NASA-TP-1049 , L-11739
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 2
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    Unknown
    Surface recession characteristics of a cryogenic insulation subjected to arc-tunnel heating (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Specimens of a cryogenic insulation, proposed for use on the space shuttle external tank, were tested in an arc tunnel over a range of heating rates, pressures, and enthalpies corresponding to the shuttle ascent environment. A regression analysis was used to correlate the test data. Correlation equations involving surface recession rate as a function of heating rate, pressure, and enthalpy were developed. These equations can be used to make total surface recession predictions for shuttle ascent flight environments.
    Keywords: NONMETALLIC MATERIALS
    Type: NASA-TM-X-3291 , L-10371
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 3
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    Unknown
    Variable mixer propulsion cycle (1978)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A design technique, method and apparatus are delineated for controlling the bypass gas stream pressure and varying the bypass ratio of a mixed flow gas turbine engine in order to achieve improved performance. The disclosed embodiments each include a mixing device for combining the core and bypass gas streams. The variable area mixing device permits the static pressures of the core and bypass streams to be balanced prior to mixing at widely varying bypass stream pressure levels. The mixed flow gas turbine engine therefore operates efficiently over a wide range of bypass ratios and the dynamic pressure of the bypass stream is maintained at a level which will keep the engine inlet airflow matched to an optimum design level throughout a wide range of engine thrust settings.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
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