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  • 1
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    Continuous Measurement of Solid Propellant Burning Rates (1966)
    American Institute of Physics
    Details
    Publication Date: 1966-01-01
    Print ISSN: 0034-6748
    Electronic ISSN: 1089-7623
    Topics: Electrical Engineering, Measurement and Control Technology , Physics
    Published by American Institute of Physics
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    PAPER CURRENT
  • 2
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    Determination of local values of gas and liquid mass flux in highly loaded two-phase flow (1974)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: A measurement system using a deceleration probe was designed for determining the local values of gas and liquid mass flux in various gas/liquid droplet sprayfields. The system was used to characterize two-phase flowfields generated by gas/liquid rocket-motor injectors. Measurements were made at static pressures up to 500 psia and injected mass flow ratios up to 20. The measurement system can also be used at higher pressures and in gas/solid flowfields.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Format: text
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    NASA TECHNICAL REPORTS
  • 3
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    Atomization and mixing characteristics of gas/liquid coaxial injector elements. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-06-27
    Description: (For abstract see issue 14, page 2291, Accession no. A71-30736)
    Keywords: PROPULSION SYSTEMS
    Type: AIAA PAPER 71-672
    Format: text
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    NASA TECHNICAL REPORTS
  • 4
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    Space storable propellant performance program coaxial injector characterization (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: An experimental program was conducted to characterize the circular coaxial injector concept for application with the space-storable gas/liquid propellant combination FLOX(82.6% F2)/CH4(g) at high pressure. The primary goal of the program was to obtain high characteristic velocity efficiency in conjunction with acceptable injector/chamber compatibility. A series of subscale (single element) cold flow and hot fire experiments was employed to establish design criteria for a 3000-lbf (sea level) engine operating at 500 psia. The subscale experiments characterized both high performance core elements and peripheral elements with enhanced injector/chamber compatibility. The full-scale injector which evolved from the study demonstrated a performance level of 99 percent of the theoretical shifting characteristic exhaust velocity with low chamber heat flux levels. A 44-second-duration firing demonstrated the durability of the injector. Parametric data are presented that are applicable for the design of circular, coaxial injectors that operate with injection dynamics (fuel and oxidizer velocity, etc.) similar to those employed in the work reported.
    Keywords: PROPELLANTS
    Type: NASA-CR-120936 , R-8973-2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 5
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    Injector design guidelines for gas/liquid propellant systems (1973)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Injector design guidelines are provided for gas/liquid propellant systems. Information was obtained from a 30-month applied research program encompassing an analytical, design, and experimental effort to relate injector design parameters to simultaneous attainment of high performance and component (injector/thrust chamber) compatibility for gas/liquid space storable propellants. The gas/liquid propellant combination studied was FLOX (82.6% F2)/ ambient temperature gaseous methane. Design criteria that provide for simultaneous attainment of high performance and chamber compatibility are presented for both injector types. Parametric data are presented that are applicable for the design of circular coaxial and like-doublet injectors that operate with design parameters similar to those employed. However, caution should be exercised when applying these data to propellant combinations whose elements operate in ranges considerably different from those employed in this study.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-120968 , R-8973-3
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Probe measures gas and liquid mass flux in high mass flow ratio two-phase flows (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Deceleration probe constructed of two concentric tubes with separator inlet operates successfully in flow fields where ratio of droplet flow rate to gas flow rate ranges from 1.0 to 20, and eliminates problems of local flow field disturbances and flooding. Probe is effective tool for characterization of liquid droplet/gas spray fields.
    Keywords: MECHANICS
    Type: LEW-11270
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Optimum design of space storable gas/liquid coaxial injectors. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Review of the results of a program of single-element, cold-flow/hot-fire experiments performed for the purpose of establishing design criteria for a high-performance gas/liquid (FLOX/CH4) coaxial injector. The approach and the techniques employed resulted in the direct design of an injector that met or exceeded the performance and chamber compatibility goals of the program without any need for the traditional 'cut-and-try' development methods.
    Keywords: PROPULSION SYSTEMS
    Type: AIAA PAPER 72-1076 , Joint Propulsion Specialist Conference; Nov 29, 1972 - Dec 01, 1972; New Orleans, LA; US
    Format: text
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    NASA TECHNICAL REPORTS
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