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  • 1
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    INVESTIGATION OF SEPARATION AND ASSOCIATED HEAT TRANSFER AND PRESSURE DISTRIBUTION ON CONE-CYLINDER-FLARE CONFIGURATIONS AT MACH FIVE (1962)
    In:  CASI
    Details
    Publication Date: 2012-03-21
    Description: Separation and heat transfer and pressure distribution on cone-cylinder-flare configurations
    Keywords: AIRCRAFT
    Format: text
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    NASA TECHNICAL REPORTS
  • 2
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    Reverse-thrust technology for variable-pitch fan propulsion systems (1976)
    In:  CASI
    Details
    Publication Date: 2016-06-07
    Description: Tests conducted to develop the technology necessary to meet the unique reverse-thrust performance requirements of a variable pitch fan propulsion system are discussed. The losses and distortion associated with the air entering the fan and core compressor from the rear of the engine, the direction of fan blade pitch rotation for best reverse-thrust aeroacoustic performance, and engine response and operating characteristics during forward- to reverse-thrust transients are among the factors studied. The test results of several scale fan models as well as a full-size variable pitch fan engine are summarized. Results show the following: a flared exhaust nozzle makes a good reverse-thrust inlet; acceptable core inlet duct recovery and distortion levels in reverse flow were demonstrated; adequate thrust levels were achieved; forward- to reverse-thrust response time achieved was better than the goal; thrust and noise levels strongly favor reverse through feather pitch; and finally, flight-type inlets make the establishment of reverse flow more difficult.
    Keywords: AERODYNAMICS
    Type: NASA. Langley Res. Center Powered-Lift Aerodyn. and Acoustics; p 387-402
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 3
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    EFFECTS OF REGENERATIVE AND RADIATION COOLING ON PERFORMANCE OF ELECTROTHERMAL THRUSTORS (1963)
    In:  CASI
    Details
    Publication Date: 2019-05-11
    Description: Effects of regenerative and radiation cooling on thrustor performance for frozen flow
    Keywords: PHYSICS, GENERAL
    Type: NASA-TN-D-1738
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 4
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    Simulation of rocket-nozzle environments with an arc-plasma generator. (1965)
    In:  Other Sources
    Details
    Publication Date: 2019-05-24
    Description: Rocket-nozzle environment simulation with DC arc- plasma generator noting graphite and phenolic material test results
    Keywords: FACILITIES, RESEARCH, AND SUPPORT
    Format: text
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    NASA TECHNICAL REPORTS
  • 5
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    Noise generated by quiet engine fans. 2: Fan A (1974)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A significant effort within the NASA Quiet Engine Program has been devoted to acoustical evaluation at the Lewis Research Center noise test facility of a family of full-scale fans. This report, documents the noise results obtained with fan A - a 1.5-pressure-ratio, 1160-ft/sec-tip-speed fan. The fan is described and some aerodynamic operating data are given. Far-field noise around the fan was measured for a variety of configurations pertaining to acoustical treatment and over a range of operating conditions. Complete results of 1/3-octave band analysis of the data are presented in tabular form. Included also are power spectra and sideline perceived noise levels. Some representative 1/3-octave band data are presented graphically, and sample graphs of continuous narrow-band spectra are also provided.
    Keywords: PROPULSION SYSTEMS
    Type: NASA-TM-X-3066 , E-7857
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 6
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    Noise generated by quiet engine fans. 3: Fan C (1976)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A family of fans designed with low noise features was acoustically evaluated, and noise results are documented for a 1.6-pressure-ratio, 472-m/sec (155-ft/sec) tip speed fan. The fan is described and some aerodynamic operating data are given. Far field noise around the fan was measured over a range of operating conditions for a variety of configurations having different arrangements of sound absorbing material in the flow ducts. Complete results of 1.3 octave band analysis of the data are presented in tabular form. Included also are acoustic power spectra and sideline perceived noise levels. Representative 1/3 octave band data are presented graphically, and sample graphs of continuous narrow band spectra are also provided.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: NASA-TM-X-3360 , E-8530
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 7
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    Studies of nozzle ablative material performance for large solid boosters Final report (1966)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: Carbon phenolic, graphite phenolic, and silica phenolic nozzle ablative materials performance for large solid propellant rocket boosters
    Keywords: PROPULSION SYSTEMS
    Type: NASA-CR-72080 , REPT.-66-2
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 8
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    Analytic and experimental evaluation of flowing air test conditions for selected metallics in a shuttle TPS application (1975)
    In:  CASI
    Details
    Publication Date: 2019-06-27
    Description: A detailed experimental and analytical evaluation was performed to define the response of TD nickel chromium alloy (20 percent chromium) and coated columbium (R512E on CB-752 and VH-109 on WC129Y) to shuttle orbiter reentry heating. Flight conditions important to the response of these thermal protection system (TPS) materials were calculated, and test conditions appropriate to simulation of these flight conditions in flowing air ground test facilities were defined. The response characteristics of these metallics were then evaluated for the flight and representative ground test conditions by analytical techniques employing appropriate thermochemical and thermal response computer codes and by experimental techniques employing an arc heater flowing air test facility and flat face stagnation point and wedge test models. These results were analyzed to define the ground test requirements to obtain valid TPS response characteristics for application to flight. For both material types in the range of conditions appropriate to the shuttle application, the surface thermochemical response resulted in a small rate of change of mass and a negligible energy contribution. The thermal response in terms of surface temperature was controlled by the net heat flux to the surface; this net flux was influenced significantly by the surface catalycity and surface emissivity. The surface catalycity must be accounted for in defining simulation test conditions so that proper heat flux levels to, and therefore surface temperatures of, the test samples are achieved.
    Keywords: METALLIC MATERIALS
    Type: NASA-CR-2531
    Format: application/pdf
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    NASA TECHNICAL REPORTS
  • 9
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    Acoustic performance of inlet multiple-pure-tone suppressors installed on NASA Quiet Engine 'C' (1977)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The purpose of the experimental program reported herein was to define the length of multiple pure tone (MPT) treatment required to reasonably suppress the MPT's produced by a supersonic tip speed fan and also determine what other suppression, broadband, and blade passing frequency (BPF), might be accomplished. The experimental results are presented in terms of both far-field and duct acoustic data. Front quadrant sound power level reduction in the far field is shown to agree with duct measurements over the range of treatment lengths. Detailed one-third octave and narrow band spectra at the maximum forward noise angle are presented. Some detailed analyses of one-third-octave band amplitudes are shown as a function of far-field angle. An approximate spinning mode duct propagation analysis is then introduced which predicts the acoustic suppression by the treatment on the multiple pure tones.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: AIAA PAPER 77-1333 , Aeroacoustics Conference; Oct 03, 1977 - Oct 05, 1977; Atlanta, GA
    Format: text
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    NASA TECHNICAL REPORTS
  • 10
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    Aerodynamic and acoustic performance of a contracting cowl high throat Mach number inlet installed on NASA Quiet Engine 'C' (1976)
    In:  Other Sources
    Details
    Publication Date: 2019-07-13
    Description: The purpose of this experimental program was to evaluate the approach and takeoff performance of a contracting cowl variable geometry design inlet installed on a high-bypass-ratio turbofan engine. The design was finalized after consideration of aerodynamic, acoustic, and mechanical factors which would lead to a viable flight-worthy inlet concept. The aerodynamic results are presented in terms of inlet recovery and distortion parameter as functions of throat Mach number, and acoustic results in terms of Perceived Noise Level. The contracting cowl high throat Mach number inlet is shown to be an attractive means to reduce forward radiated noise from a high bypass ratio turbofan engine.
    Keywords: AERODYNAMICS
    Type: AIAA PAPER 76-540 , Aero-Acoustics Conference; Jul 20, 1976 - Jul 23, 1976; Palo Alto, CA
    Format: text
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    NASA TECHNICAL REPORTS
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