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  • 1
    Publication Date: 2019-06-28
    Description: A series of tests has been carried out to investigate the effects of various scale parameters on the direct connect scramjet combustor performance. The calculated combustion efficiency appears to be independent of scale for the same geometry, but tests with more precise scaling of the entire combustor are required to verify this. Combustion, however, can be strongly dependent on geometry for the same scale. It is suggested that the beneficial aspects of certain geometric or scale variations can be combined to improve the overall performance.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 87-2164
    Format: text
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  • 2
    Publication Date: 2019-07-13
    Description: The present test series was conducted to ascertain the effects of various scale and geometric parameters on the combustion and pressure rise limits of a direct-connect supersonic combustor employing hydrogen fuel in a Mach 2 flow and 1-atm static pressure. The injector configuration was similar to that developed by Wagner et al. (1987). Attention is given to the effects of upstream length, fuel-injection gap, and constant-area combustor length, as well as to those of equivalence ratios and stagnation temperature. It is found that, for a given scale, combustion can be strongly dependent on such geometric factors as the use of either constant-area combustion or immediate expansion.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: ICAS Congress; Aug 28, 1988; Jerusalem; Israel
    Format: text
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  • 3
    Publication Date: 2019-07-10
    Description: This White Paper examines the current state of Hypersonic Airbreathing Propulsion at the NASA Langley Research Center and the factors influencing this area of work and its personnel. Using this knowledge, the paper explores beyond the present day and suggests future directions and strategies for the field. Broad views are first taken regarding potential missions and applications of hypersonic propulsion. Then, candidate propulsion systems that may be applicable to these missions are suggested and discussed. Design tools and experimental techniques for developing these propulsion systems are then described, and approaches for applying them in the design process are considered. In each case, current strategies are reviewed and future approaches that may improve the techniques are considered. Finally, the paper concentrates on the needs to be addressed in each of these areas to take advantage of the opportunities that lay ahead for both the NASA Langley Research Center and the Aerodynamic Aerothermodynamic, and Aeroacoustics Competency. Recommendations are then provided so that the goals set forth in the paper may be achieved.
    Keywords: Aircraft Propulsion and Power
    Type: NASA/TM-2002-211951 , L-18110 , NAS 1.15:211951
    Format: application/pdf
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