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  • 1975-1979  (4)
  • 1
    facet.materialart.
    Unknown
    Studies of scramjet/airframe integration techniques for hypersonic aircraft (1975)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: New design and analysis techniques for engine-airframe integration were applied in a recent hypersonic vehicle design study. A new technique was developed to design the vehicle's forebody so that uniform precompressed flow was produced at the inlet entrance. Results are verified with three-dimensional characteristic calculations. Results from a new three-dimensional method for calculating nozzle flows show that the entire lower afterbody of the vehicle can be used as a scramjet exhaust nozzle to achieve efficient, controlled, and stable flight over a wide range of flight conditions.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 75-58 , American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting; Jan 20, 1975 - Jan 22, 1975; Pasadena, CA
    Format: text
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 2
    facet.materialart.
    Unknown
    Subsonic longitudinal aerodynamic characteristics and engine pressure distributions for an aircraft with an integrated scramjet designed for Mach 6 cruise (1977)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A 1/10-scale model of a proposed hypersonic aircraft with an integrated scramjet was tested. The investigation took place over a Mach number range from 0.2 to 0.7 and an angle of attack range from 2 deg to approximately 17 deg at a sideslip angle of 0 deg. The primary configuration variables studied were engine location, internal engine geometry, and external engine geometry. The results are presented without analysis.
    Keywords: AERODYNAMICS
    Type: NASA-TM-X-73911
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 3
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    Unknown
    Scramjet nozzle design and analysis as applied to a highly integrated hypersonic research airplane (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Engine-nozzle airframe integration at hypersonic speeds was conducted by using a high-speed research aircraft concept as a focus. Recently developed techniques for analysis of scramjet-nozzle exhaust flows provide a realistic analysis of complex forces resulting from the engine-nozzle airframe coupling. By properly integrating the engine-nozzle propulsive system with the airframe, efficient, controlled and stable flight results over a wide speed range.
    Keywords: AERODYNAMICS
    Type: NASA-TN-D-8334 , L-11003
    Format: application/pdf
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
  • 4
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    Unknown
    Effect of an integrated scramjet installation on the subsonic performance of an aircraft designed to Mach 6 cruise (1977)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Various factors contributing to the high drag caused by the installation of a six-module scramjet engine were determined from wind tunnel tests at Mach numbers from 0.2 to 0.7. Methods for alleviating this drag were also explored. The external exhaust nozzle, required for good cruise performance, was a major contributor. Of the drag produced by the engine modules, a significant fraction was attributable to wall divergence in the combustor. Good drag simulation could be achieved by using a single fuel injection strut having approximately the same cross-sectional area as the three used on the full-scale engine. External exhaust nozzle fences had a small but beneficial effect on maximum L/D and a flap which diverted the flow away from the inlet was effective in decreasing drag but only at low angles of attack.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 77-1230 , Aircraft Systems and Technology Meeting; Aug 22, 1977 - Aug 24, 1977; Seattle, WA
    Format: text
    Location Call Number Expected Availability
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    NASA TECHNICAL REPORTS
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