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  • 11
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    Two-dimensional cascade investigation of a turbine tandem blade design (1969)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Flow and wake characteristics on turbine tandem blades in two dimensional cascade tunnel
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-1836
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 12
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    Shuttle airbreathing propulsion (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Requirements analysis of airbreathing gas turbine engines for shuttle vehicles
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-67806
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 13
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    Two-dimensional cascade test of a jet-flap turbine rotor blade (1971)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Two dimensional cascade test of jet flap turbine rotor blade
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-2183 , E-5989
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 14
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    Shuttle airbreathing propulsion (1971)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Space shuttle airbreathing propulsion systems requirements and design studies, considering cruise, landing, go-around and ferry capabilities
    Keywords: PROPULSION SYSTEMS
    Type: AIAA PAPER 71-662 , PROPULSION JOINT SPECIALIST CONFERENCE; Jun 14, 1971 - Jun 18, 1971; SALT LAKE CITY, UT; US
    Format: text
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 15
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    Airbreathing engines for space shuttle. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The requirements imposed on the airbreathing engines by the shuttle mission and some results from engine design studies are discussed. In particular, some of the engine system weight study results are presented, potential problem areas and required engine modifications are identified, and testing requirements for a development and qualification program are discussed. The engines of interest for the shuttle are engines that are currently being developed for other applications. The potential problems, engine modifications, and testing requirements result primarily from the new environments associated with launch, space residence, and reentry.
    Keywords: SPACE VEHICLES
    Type: JANNAF Propulsion Meeting; Nov 27, 1972 - Nov 29, 1972; New Orleans, LA
    Format: text
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 16
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    Airbreathing engines for Space Shuttle. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The requirements imposed on the airbreathing engines by the shuttle mission and some results from engine design studies are discussed. In particular some of the engine system weight study results are presented, potential problem areas and required engine modifications are identified, and testing requirements for a development and qualification program are discussed. The engines of interest for the shuttle are engines that are currently being developed for other applications. The potential problems, engine modifications, and testing requirements result primarily from the new environments associated with launch, space residence, and reentry.
    Keywords: PROPULSION SYSTEMS
    Type: SAE PAPER 720805 , National Aerospace Engineering and Manufacturing Meeting; Oct 02, 1972 - Oct 05, 1972; San Diego, CA
    Format: text
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 17
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    A turbojet simulator for Mach numbers up to 2.0. (1972)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A turbojet simulator has been designed and fabricated for use in wind tunnel models. The simulator contains a six-stage, axial-flow compressor powered by a three-stage, axial-flow turbine. High pressure heated air was used to drive the turbine. At design conditions, compressor axial flow, turbine exit flow, and a third supplementary flow all entered the exhaust nozzle at equal values of pressure and temperature. Overall aerodynamic design, instrumentation, and calibration procedure is presented. Performance of the device when used to simulate a J-85 turbojet engine at transonic speeds is reported. The installed nozzle performance obtained with the simulator is also discussed and compared with flight data.
    Keywords: PROPULSION SYSTEMS
    Type: ASME PAPER 72-GT-89 , American Society of Mechanical Engineers, Gas Turbine and Fluids Engineering Conference and Products Show; Mar 26, 1972 - Mar 30, 1972; San Francisco, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 18
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    A turbojet simulator for Mach numbers up to 2.0 (1972)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: A turbojet simulator was designed and fabricated for use in wind tunnel models. The simulator contains a six-stage, axial-flow compressor powered by a three-stage, axial-flow turbine. High pressure heated air was used to drive the turbine. At design conditions, compressor axial flow, turbine exit flow, and a third supplementary flow all entered the exhaust nozzle at equal values of pressure and termperature. Overall aerodynamic design, compressor operating conditions, automatic controls, turbine aerodynamic design, instrumentation, and calibration procedure is presented. Performance of the device when used to simulate a J-85 turbojet engine at transonic speeds is reported. The installed nozzle performance obtained with the simulator is also discussed and compared with flight data.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-67973 , E-6690 , Ann. Intern. Gas Turbine Conf. and Products Show; Mar 23, 1972 - Mar 30, 1972; San Francisco, CA; United States
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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