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  • AIRCRAFT PROPULSION AND POWER
  • Meteorology and Climatology
  • 2005-2009
  • 1975-1979
  • 1970-1974  (15)
  • 1950-1954
  • 1974  (15)
Collection
Keywords
Years
  • 2005-2009
  • 1975-1979
  • 1970-1974  (15)
  • 1950-1954
Year
  • 1
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    Reliability of laboratory tests of VSTOL and other long duration noises (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Paired-comparison and magnitude estimations of the subjective noisiness or unacceptability of noise from fixed wing jet aircraft and simulated noise of VSTOL aircraft were obtained from groups of subjects given different instructions. These results suggest that VSTOL noises can be evaluated in terms of their noisiness or unwantedness to people with reasonable accuracy by units of the physical measures designated as PNdBM, with or without tone corrections, and dBD sub 2. Also, that consideration should be given to the use of D sub 2 as an overall frequency weighting function for sound level meters instead of the presently available A weighting. Two new units of noise measurement, PLdB and dB(E), used for predicting subjective noisiness, were found to be less accurate than PNdBM or dBD sub 2 in this regard.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-2471
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 2
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    Wind tunnel test of model target thrust reversers for the Pratt and Whitney aircraft JT8D-100 series engines installed on a 727-200 airplane (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: The results of a low speed wind tunnel test of 0.046 scale model target thrust reversers installed on a 727-200 model airplane are presented. The full airplane model was mounted on a force balance, except for the nacelles and thrust reversers, which were independently mounted and isolated from it. The installation had the capability of simulating the inlet airflows and of supplying the correct proportions of primary and secondary air to the nozzles. The objectives of the test were to assess the compatibility of the thrust reversers target door design with the engine and airplane. The following measurements were made: hot gas ingestion at the nacelle inlets; model lift, drag, and pitching moment; hot gas impingement on the airplane structure; and qualitative assessment of the rudder effectiveness. The major parameters controlling hot gas ingestion were found to be thrust reverser orientation, engine power setting, and the lip height of the bottom thrust reverser doors on the side nacelles. The thrust reversers tended to increase the model lift, decrease the drag, and decrease the pitching moment.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-134709 , D6-41900
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    Modifications that improve performance of a double annular combustor at simulated engine idle conditions (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Techniques were evaluated to determine if simple combustor modifications could be used to reduce the engine ground idle emissions of a double annular combustor designed for Mach 3.0 cruise operation. These techniques were radial fuel staging, the use of radial-inflow rather than axial-flow air swirlers, and the optimization of fuel-nozzle spray angle and differential pressure. Radial fuel staging and the use of radial-inflow air swirlers significantly improved performance at two ground idle test conditions simulating both low- and high-compression ratio engines.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-3127 , E-7960
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Performance of a model cascade thrust reverser for short-haul applications (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Aerodynamic and acoustic characteristics are presented for a cowl-mounted, model cascade thrust reverser suitable for short-haul aircraft. Thrust reverser efficiency and the influence on fan performance were determined from isolated fan-driven models under static and forward velocity conditions. Cascade reverser noise characteristics were determined statically in an isolated pipe-flow test, while aerodynamic installation effects were determined with a wind-tunnel, fan-powered airplane model. Application of test results to short-haul aircraft calculations demonstrate that such a cascade thrust reverser may be able to meet both the performance and noise requirements for short-haul aircraft operation. However, aircraft installation effects can be quite significant.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 74-1171 , American Institute of Aeronautics and Astronautics and Society of Automotive Engineers, Propulsion Conference; Oct 21, 1974 - Oct 23, 1974; San Diego, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Influence of mixer nozzle velocity decay characteristics on CTOL-OTW jet noise shielding (1974)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Jet noise shielding benefits for CTOL engine-over-the-wing configurations were obtained with model scale multitube and lobed mixer nozzles and various shielding surface geometries. Spectral data were obtained with jet velocities from 585 to 1110 ft/sec. Correlation equations for predicting jet noise shielding benefits with single conical nozzle installations were modified to correlate the mixer nozzle data. The modification included consideration of the number of nozzle elements and the peak axial velocity decay in the flow field adjacent to the shielding surface. The effect of forward velocity on jet noise attenuation by a shielding surface is discussed.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-71631 , E-8168 , Aerospace Sci. Meeting; Jan 20, 1975 - Jan 22, 1975; Pasadena, CA; United States
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Titanium honeycomb acoustic lining structural and thermal test report (1974)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: The results are presented of static, fatigue and thermal testing of titanium honeycomb acoustic panels representing the acoustic tailpipe for the Pratt and Whitney Aircraft JT8D Refan engine which is being studied for use on the Boeing 727-200 airplane. Test specimens represented the engine and tailpipe flange joints, the rail to which the thrust reverser is attached and shear specimens of the tailpipe honeycomb. Specimens were made in four different batches with variations in configuration, materials and processes in each. Static strength of all test specimens exceeded the design ultimate load requirements. Fatigue test results confirmed that aluminum brazed titanium, as used in the Refan tailpipe design, meets the fatigue durability objectives. Quality of welding was found to be critical to life, with substandard welding failing prematurely, whereas welding within the process specification exceeded the panel skin life. Initial fatigue testing used short grip length bolts which failed prematurely. These were replaced with longer bolts and subsequent testing demonstrated the required life. Thermal tests indicate that perforated skin acoustic honeycomb has approximately twice the heat transfer of solid skin honeycomb.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-134783 , D6-42352
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Advanced supersonic technology concept study: Hydrogen fueled configuration (1974)
    In:  CASI
    Details
    Publication Date: 2019-07-13
    Description: Conceptual designs of hydrogen fueled supersonic transport configurations for the 1990 time period were developed and compared with equivalent technology Jet A-1 fueled vehicles to determine the economic and performance potential of liquid hydrogen as an alternate fuel. Parametric evaluations of supersonic cruise vehicles with varying design and transport mission characteristics established the basis for selecting a preferred configuration which was then studied in greater detail. An assessment was made of the general viability of the selected concept including an evaluation of costs and environmental considerations, i.e., exhaust emissions and sonic boom characteristics. Technology development requirements and suggested implementation schedules are presented.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-CR-114718 , LR-26323
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Quasi-three-dimensional flow solution by meridional plane analysis (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: A computer program has been developed to obtain subsonic or shock-free transonic, nonviscous flow analysis on the hub-shroud midchannel flow surface of a turbomachine. The analysis may be for any annular passage, with or without blades. The blades may be fixed or rotating and may be twisted and leaned. The flow may be axial, radial, or mixed. Blade surface velocities over the entire blade are approximated, based on the rate of change of angular momentum. This gives a three-dimensional flow picture based on a two-dimensional analysis. This paper discusses the method used for the program and shows examples of the type of passages and blade rows which can be analyzed. Also, some numerical examples are given to show how the program can be used for practical assistance in design of blading, annular passages, and annular diffusers.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: SAE PAPER 740850 , Society of Automotive Engineers, National Aerospace Engineering and Manufacturing Meeting; Oct 01, 1974 - Oct 03, 1974; San Diego, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 9
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    Emission calibration of a J-58 afterburning turbojet engine at simulated supersonic, stratospheric flight conditions (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Emissions of total oxides of nitrogen, unburned hydrocarbons, and carbon monoxide from a J-58 engine at simulated flight conditions of Mach 2.0, 2.4, and 2.8 at 19.8 km altitude are reported. For each flight condition, measurements were made for four engine power levels from maximum power without afterburning through maximum afterburning. These measurements were made 7 cm downstream of the engine primary nozzle using a single point traversing gas sample probe. Results show that emissions vary with flight speed, engine power level, and with radial position across the exhaust.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: International Conference on the Environmental Impact of Aerospace Operations in the High Atmosphere; Jul 08, 1974 - Jul 10, 1974; San Diego, CA
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Effect of forward velocity on the noise characteristics of dual-flow jet nozzles (1974)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: Acoustic results of jet noise tests conducted on scale-model nozzles at a wall isolation facility are presented and analyzed. The test fixture featured a triple-flow system for the purpose of simulating freestream flow around hot dual-flow jet nozzles. Test nozzles included 1/20th scale models of the exhaust system for the JT8D-9 engine, power plant for the Boeing 727 airplane (bypass ratio 1) and of the JT8D-109 refan engine (bypass ratio 2). It was found that overall jet noise is reduced by the forward velocity in proportion to the fifth and sixth power of the relative primary jet velocity. Spectral and directivity characteristics are presented.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: ASME PAPER 74-WA/AERO-4 , American Society of Mechanical Engineers, Winter Annual Meeting; Nov 17, 1974 - Nov 22, 1974; New York, NY
    Format: text
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    NASA TECHNICAL REPORTS
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