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  • FLUID MECHANICS AND HEAT TRANSFER  (4)
  • SPACECRAFT PROPULSION AND POWER  (1)
  • 1
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    Scramjet sidewall burning: Preliminary shock tunnel results (1985)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Experiments performed with a two dimensional model scramjet with particular emphasis on the effect of fuel injection from a wall are reported. Air low with a nominal Mach number of 3.5 and varied enthalpies was produced. It was found that neither hydrogen injection angle nor combustor divergence angle had any appreciable effect on thrust values while increased combustor length appeared to increase thrust levels. Specific impulse was observed to peak when hydrogen was injected at an equivalence ratio of about 2. Lowering the Mach number of the injected hydrogen at low equivalence ratios, less than 4, appeared to benefit specific impulse while hydrogen Mach number had little effect at higher equivalence ratios. When a 1:1 mixture by volume of nitrogen and oxygen is used instead of air as a test gas, it is found that hydrogen combustion is enhanced but only at high enthalpies.
    Keywords: SPACECRAFT PROPULSION AND POWER
    Type: NASA-CR-176420 , NAS 1.26:176420 , REPT-12/85
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Shock tunnel studies of scramjet phenomena, supplement 6 (1993)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Reports by the staff of the University of Queensland on various research studies related to the advancement of scramjet technology are presented. These reports document the tests conducted in the reflected shock tunnel T4 and supporting research facilities that have been used to study the injection, mixing, and combustion of hydrogen fuel in generic scramjets at flow conditions typical of hypersonic flight. In addition, topics include the development of instrumentation and measurement technology, such as combustor wall shear and stream composition in pulse facilities, and numerical studies and analyses of the scramjet combustor process and the test facility operation.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-191428 , NAS 1.26:191428
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Shock Tunnel Studies of Scramjet Phenomena 1993 (1995)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Reports by the staff of the University of Queensland on various research studies related to the advancement of scramjet technology and hypervelocity pulse test facilities are presented. These reports document the tests conducted in the reflected shock tunnel T4 and supporting research facilities that have been used to study the injection, mixing, and combustion of hydrogen fuel in generic scramjets at flow conditions typical of hypersonic flight. In addition, topics include the development of instrumentation and measurement technology, such as combustor wall shear and stream composition in pulse facilities, and numerical studies and analyses of the scramjet combustor process and the test facility operation. This research activity is Supplement 10 under NASA Grant NAGw-674.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-195038 , NAS 1.26:195038
    Format: application/pdf
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  • 4
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    Shock tunnel studies of scramjet phenomena, supplement 7 (1993)
    In:  CASI
    Details
    Publication Date: 2019-06-28
    Description: Reports by the staff of the University of Queensland on various research studies related to the advancement of scramjet technology are presented. These reports document the tests conducted in the reflected shock tunnel T4 and supporting research facilities that have been used to study the injection, mixing, and combustion of hydrogen fuel in generic scramjets at flow conditions typical of hypersonic flight. In addition, topics include the development of instrumentation and measurement technology, such as combustor wall shear and stream composition in pulse facilities, and numerical studies and analyses of the scramjet combustor process and the test facility operation. This research activity is Supplement 7 under NASA Grant NAGW-674.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: NASA-CR-191572 , NAS 1.26:191572
    Format: application/pdf
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  • 5
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    Test flow disturbances in an expansion tube (1992)
    In:  Other Sources
    Details
    Publication Date: 2019-08-27
    Description: The operation of an expansion tube is investigated theoretically with emphasis on the factors that have limited the utility of the expansion tube in the past. It is shown why the window of steady test conditions is narrow and how this window can be expanded so that these facilities can be used in a variety of hypersonic research. The theoretical predictions are supported by centerline Pitot pressure measurements using air as the test gas.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: Journal of Fluid Mechanics (ISSN 0022-1120); p. 493-521.
    Format: text
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