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  • Aircraft Propulsion and Power
  • 2020-2023
  • 2015-2019
  • 1980-1984
  • 1960-1964  (4)
  • 1945-1949
  • 1960  (4)
  • 1
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    Factors that Affect Operational Reliability of Turbojet Engines (1960)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: The problem of improving operational reliability of turbojet engines is studied. Failure statistics for this engine are presented, the theory and experimental evidence on how engine failures occur are described, and the methods available for avoiding failure in operation are discussed.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-TR-R-54
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 2
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    Static Thrust of an Annular Nozzle with a Concave Central Base (1960)
    In:  CASI
    Details
    Publication Date: 2019-08-17
    Description: A static test of an annular nozzle with a concave central base, producing a jet in which tangents to the jet streamlines at the exit converged toward a region on the axis of symmetry downstream of the exit, has indicated good thrust performance. A value of nozzle-flow coefficient only slightly less than unity indicates the internal loss to be small. Pressures on the concave central base are relatively large and positive, and a predictable portion of the total thrust of the jet is exerted on the central base.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-TN-D-418 , L-851
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 3
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    Internal-Performance Evaluation of Two Fixed-Divergent-Shroud Ejectors (1960)
    In:  CASI
    Details
    Publication Date: 2019-08-15
    Description: Ejectors designed for use in a Mach 2.2 aircraft were evaluated over a range of representative primary pressure ratios and ejector corrected weight-flow ratios. Basic thrust and pumping characteristics are discussed in terms of an assumed engine operating schedule to illustrate the variation of performance with Mach number. The two designs differed about 16 percent in the shroud longitudinal spacing ratio. For corrected ejector weight-flow ratios up to 0.10, the performance of the fixed-shroud ejector designs is comparable with that of a similar continuously variable ejector except at conditions corresponding to acceleration with afterburning from Mach 0.4 to 1.2. In this region, the ejector thrust ratio decreased to a minimum of 0.96.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-TM-X-257 , E-691
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 4
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    Internal Performance Evaluation of a Two Position Divergent Shroud Ejector (1960)
    In:  CASI
    Details
    Publication Date: 2019-08-16
    Description: A two-position divergent shroud ejector was investigated in an unheated quiescent-air facility over a range of operational variables applicable to a Mach 2.5 aircraft. The performance data are shown in terms of hypothetical engine operating conditions to illustrate variations of performance with Mach number. The overall thrust performance was reasonably good, with ejector thrust ratios ranging from 0.97 to 0.98 for all conditions except that corresponding to acceleration with afterburning through the transonic flight Mach number region from 0.9 to 1.1, where the ejector thrust ratio decreased to as low as 0.945 for an ejector corrected weight-flow ratio of 0.105.
    Keywords: Aircraft Propulsion and Power
    Type: NASA-TM-X-258 , E-753
    Format: application/pdf
    Location Call Number Expected Availability
    BibTip Others were also interested in ...
    NASA TECHNICAL REPORTS
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