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  • PROPULSION SYSTEMS  (118)
  • ASTROPHYSICS
  • 1970-1974  (118)
  • 1972  (52)
  • 1971  (66)
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  • 1970-1974  (118)
Year
  • 11
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    Supersonic exhaust nozzles (1971)
    In:  CASI
    Details
    Publication Date: 2006-04-20
    Description: Design and characteristics of exhaust system for supersonic aircraft
    Keywords: PROPULSION SYSTEMS
    Type: AIRCRAFT PROPULSION 1971; P 233-282
    Format: text
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    NASA TECHNICAL REPORTS
  • 12
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    Low cost engines for aircraft (1971)
    In:  CASI
    Details
    Publication Date: 2006-04-20
    Description: Development and characteristics of low cost engines for general aviation aircraft
    Keywords: PROPULSION SYSTEMS
    Type: AIRCRAFT PROPULSION 1971; P 211-231
    Format: text
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    NASA TECHNICAL REPORTS
  • 13
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    Sound propagation and absorption in foam - A distributed parameter model. (1971)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Liquid-base foams are highly effective sound absorbers. A better understanding of the mechanisms of sound absorption in foams was sought by exploration of a mathematical model of bubble pulsation and coupling and the development of a distributed-parameter mechanical analog. A solution by electric-circuit analogy was thus obtained and transmission-line theory was used to relate the physical properties of the foams to the characteristic impedance and propagation constants of the analog transmission line. Comparison of measured physical properties of the foam with values obtained from measured acoustic impedance and propagation constants and the transmission-line theory showed good agreement. We may therefore conclude that the sound propagation and absorption mechanisms in foam are accurately described by the resonant response of individual bubbles coupled to neighboring bubbles.
    Keywords: PROPULSION SYSTEMS
    Type: Acoustical Society of America; vol. 50
    Format: text
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    NASA TECHNICAL REPORTS
  • 14
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    Swirling base injection for supersonic combustion ramjets. (1972)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Experimental evaluation of the swirling base injection proposed by Swithenbank and Chigier (1969) for application in supersonic combustion ramjets or scramjets. This concept of accelerated mixing in supersonic streams through swirl was tested, but the results indicate that swirl does not produce any enhancement of mixing.
    Keywords: PROPULSION SYSTEMS
    Type: AIAA Journal; 10; Sept
    Format: text
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    NASA TECHNICAL REPORTS
  • 15
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    Acoustic Analysis of Solid Rocket Motor Cavities by a Finite Element Method (1971)
    In:  CASI
    Details
    Publication Date: 2014-09-03
    Description: Adaptation of NASTRAN program to solve acoustic mode problems of solid rocket motor cavities by finite element method
    Keywords: PROPULSION SYSTEMS
    Type: NASA. Langley Res. Center NASTRAN: Users Experiences; p 285-324
    Format: text
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    NASA TECHNICAL REPORTS
  • 16
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    Experimental quiet engine program aerodynamic performance of Fan C (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: This report presents the aerodynamic component test results of Fan C, a high-bypass-ratio, low-aerodynamic-loading, 1550 feet per second (472.4 m/sec), single-stage fan, which was designed and tested as part of the NASA Experimental Quiet Engine Program. The fan was designed to deliver a bypass pressure ratio of 1.60 with an adiabatic efficiency of 84.2 percent at a total fan flow of 915 lb/sec (415.0 kg/sec). It was tested with and without inlet distortion. A bypass total-pressure ratio of 1.61 and an adiabatic efficiency of 83.9 percent at a total fan flow of 921 lb/sec (417.8 kg/sec) were actually achieved. An operating margin in excess of 14.6 percent was demonstrated at design speed.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-120981
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 17
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    Experimental dynamic response of a two-dimensional, Mach 2.7, mixed compression inlet (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A test program was conducted on a two-dimensional supersonic inlet. Internal disturbances in diffuser exit mass flow were produced by oscillating overboard bypass doors. Open-loop dynamic responses of shock position, throat exit and diffuser exit static pressures are presented. The steady-state and dynamic coupling between ducts were also obtained. The experimental results from the two-dimensional inlet are compared to results from a similar size axisymmetric inlet and also to a transfer function synthesis program.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TN-D-6957 , E-7002
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 18
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    High-loading, 1800 ft/sec tip speed transonic compressor fan stage. 1: Aerodynamic and mechanical design (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A single stage fan with a tip speed of 1800 ft/sec (548.6m/sec) and hub/tip ratio of 0.5 was designed to produce a pressure ratio of 2.285:1 with an adiabatic efficiency of 84.0%. The design flow per inlet annulus area is 38.7 lbm/sq ft-sec (188.9KG/sqm-sec). Rotor blades have modified multiple-circular-arc and precompression airfoil sections. The stator vanes have multiple-circular-arc airfoil sections.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-120907 , PWA-4534
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 19
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    Experimental quiet engine program aerodynamic performance of Fan B (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: This report presents the aerodynamic component test results of Fan B, one of two high-bypass-ratio, 1160 feet per second (353.6 m/sec) single-stage fans, which was designed and tested as part of the NASA Experimental Quiet Engine Program. The fan was designed to deliver a bypass pressure ratio of 1.50 with an adiabatic efficiency of 87.0% at a total fan flow of 950 lb/sec (430.9 kg/sec). It was tested with and without inlet distortion. A bypass total pressure ratio of 1.52 and an adiabatic efficiency of 86.9% at a total fan flow of 966 lb/sec (438.2 kg/sec) were actually achieved. An operating margin of 19.5% was demonstrated at design speed.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-72993
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 20
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    Digital-computer normal shock position and restart control of a Mach 2.5 axisymmetric mixed-compression inlet (1972)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Digital computer control of a mixed-compression inlet is discussed. The inlet was terminated with a choked orifice at the compressor face station to dynamically simulate a turbojet engine. Inlet diffuser exit airflow disturbances were used. A digital version of a previously tested analog control system was used for both normal shock and restart control. Digital computer algorithms were derived using z-transform and finite difference methods. Using a sample rate of 1000 samples per second, the digital normal shock and restart controls essentially duplicated the inlet analog computer control results. At a sample rate of 100 samples per second, the control system performed adequately but was less stable.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TN-D-6880 , E-6498
    Format: application/pdf
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