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  • 11
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    Development of propulsion for high atmospheric pressure or dense environments (1973)
    In:  CASI
    Details
    Publication Date: 2006-02-22
    Description: The development of a propulsion system that employs a detonating propellant is described, and the need for such a system and its use in certain planetary atmospheres are demonstrated. A theoretical formulation of the relevant gas-dynamic processes was developed, and a related series of experimental tests were pursued.
    Keywords: PROPULSION SYSTEMS
    Type: JPL Quart. Tech. Rev., Vol. 3, No. 2 (NASA-CR-133863); p 45-52
    Format: text
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  • 12
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    Tone generation by aeroacoustic sources in pipes with flow (1990)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: Sound production by axisymmetric ring cavities in internal flow has been investigated experimentally. These ring sources generate sound when the acoustic motion in the cavity is in resonance in one of many possible modes. Experimental results agree with predictions of a model eddy-driven oscillator. It is observed that the standing waves produced by reflections from regions upstream and downstream of the source are adjusted by the source such that the source is at a pressure antinode at the condition of maximum sound emission.
    Keywords: ACOUSTICS
    Type: Acoustical Society of America, Journal (ISSN 0001-4966); 87; 1489-149
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  • 13
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    Aeroacoustic flow sensor (1991)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: A theoretical analysis of standing waves in a pipe with flow was conducted aimed toward the development of a flowmeter based on a measurement of phase difference between two points on the circumference of a pipe separated axially by an integral multiple of half sound wavelength. Effects of nonzero Mach number, variable ratios of upstream and downstream running waves, choice of location of the sensing pressure taps, and the incorrect spacings were examined numerically. Calculations were also made for steam flow where the maximum Mach number is much smaller than in cold air flows. For an industrial application where steam flow velocities are below 50 m/s, a very accurate sensor is shown to be possible. Experimental data were obtained by using an active aeroacoustic source over the range of 50 m/s to zero in an air flow. Experimental phase plots obtained from several coast-down tests have been compared with analytical results. The agreement with theory is excellent when the spacings are near N(lambda)/2 and the sensing locations are near the pressure antinodes. Otherwise, some zero shifts are introduced. Theory predicts that for steam flow much better results can be expected because the maximum Mach number is much smaller. Effects due to the (1-M-squared) factor would be imperceptible for steam flow.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: Review of Scientific Instruments (ISSN 0034-6748); 62; 2205-221
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  • 14
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    On the reverse flow ceiling jet in pool fire-ventilation crossflow interactions in a simulated aircraft cabin interior (1989)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: The behavior of the reverse flow ceiling jet against the ventilation flow from 0.58 to 0.87 m/s was investigated in a 1/3 scale model of a wide body aircraft interior. For all tests, strong reverse-flow ceiling jets of hot gases were detected well upstream of the fire. Both thicknesses of the reverse-flow ceiling jet and the smoke layer increased with the fire-crossflow parameter. The thickness of the smoke layer where the smoke flows along the main flow below the reverse-flow ceiling jet was almost twice that of the reverse-flow ceiling jet. Detailed spatial and time-varying temperatures of the gas in the test section were measured, and velocity profiles were also measured using a temperature compensated hot film.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Format: text
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  • 15
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    Pool fires in a simulated aircraft cabin interior with ventilation (1987)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Description: Results of experiments conducted at the JPL to evaluate aircraft postcrash fire hazards are presented. The experiments were carried out in a one-third scale simulated aircraft cabin geometry to study pool fire and ventilation flow interactions. It is shown that wind-induced ventilation may significantly affect fire plume orientation, smoke transport, and heat fluxes and thus will affect subsequent fire spread and the immediate survivability of the passengers.
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: Journal of Aircraft (ISSN 0021-8669); 24; 470-472
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  • 16
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    Measurements of the response of transport aircraft ceiling panels to fuel fires (1986)
    In:  Other Sources
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    Publication Date: 2011-08-19
    Keywords: AIR TRANSPORTATION AND SAFETY
    Type: Journal of Aircraft (ISSN 0021-8669); 23; 207-212
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  • 17
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    High-intensity tone generation by aeroacoustic sources (1987)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: An experimental investigation has been carried out on the production of high-intensity tones by axisymmetric ring cavities. Maximum sound production occurs during an acoustic resonance at Strouhal numbers, which depend only on the local flow velocity independent of cavity location. Values of sound pressure of about 115 dB at 1-m distance can be generated by axisymmetric ring cavities on projectiles moving at a relatively low flight speed equal to 70 m/s. Frequencies in the audible range up to several kilohertz can be generated aeroacoustically. A simple analytical model has been developed to explain the experimental observations.
    Keywords: ACOUSTICS
    Type: Acoustical Society of America, Journal (ISSN 0001-4966); 82; 2075-208
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  • 18
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    Analog circuit for the measurement of phase difference between two noisy sine-wave signals (1989)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: A simple circuit was designed to measure the phase difference between two noisy sine waves. It locks over a wide range of frequencies and produces an output proportional to the phase difference of rapidly varying signals. A square wave locked in frequency and phase to the first signal is produced by a phase-locked loop and is amplified by an operational amplifier.
    Keywords: ELECTRONICS AND ELECTRICAL ENGINEERING
    Type: Review of Scientific Instruments (ISSN 0034-6748); 60; 3081-308
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  • 19
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    Acoustic temperature profile measurement technique for large combustion chambers (1989)
    In:  Other Sources
    Details
    Publication Date: 2011-08-19
    Description: Measurement of times of flight of sound waves can be used to determine temperatures in a gas. This paper describes a system, based on this principle, that is capable of giving the temperature profile in a nonisothermal gas volume, for example, prevalent in a large furnace. The apparatus is simple, rugged, accurate, and capable of being automated for process control applications. It is basically an acoustic waveguide where the outside temperature profile is transferred to a chosen gas contained inside the guide.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: ASME, Transactions, Journal of Heat Transfer (ISSN 0022-1481); 111; 461-466
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  • 20
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    Viscous slipstream flow downstream of a centerline Mach reflection (1971)
    In:  Other Sources
    Details
    Publication Date: 2011-08-16
    Description: Viscous slipstream flow downstream of triple shock wave intersection in supersonic diffuser air flow, using Pitot and static pressure probe measurements
    Keywords: AERODYNAMICS
    Type: ; - ASTRONOMY 1969- TE
    Format: text
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