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  • 1
    Electronic Resource
    Electronic Resource
    New York, NY : American Institute of Physics (AIP)
    Physics of Fluids 1 (1989), S. 1240-1248 
    ISSN: 1089-7666
    Source: AIP Digital Archive
    Topics: Physics
    Notes: The effect of the initial turbulence level on the development of an axisymmetric jet was experimentally investigated. The turbulence intensity at the jet exit was varied, over the range 0.15%–5%, by using screens and grids placed upstream of an 8.8 cm diam nozzle. Top-hat initial mean velocity profiles with approximately identical boundary layer states were ensured in all cases; the turbulence was homogeneous and the spectra were broadband. It was found, contrary to earlier reports, that the natural jet evolution remained essentially unchanged for varying initial turbulence intensities. The response of the jet to single frequency, plane wave excitation was then studied over the full range of initial turbulence intensities. It was found that for even the highest turbulence (5%), the jet was quite excitable and could be influenced measurably by a tone of small amplitude. However, the jet "excitability,'' as assessed from the variations of the mean velocity as well as the total and fundamental rms amplitudes on the axis, diminished with increasing initial turbulence. As the initial turbulence was increased, the amplitude of the discrete tone had to be increased in order to achieve the same excited state of the jet. It was also found that there existed a limit to the jet excitability, beyond which no additional effect could be achieved, as the amplitude of the discrete tone was increased. Results are also shown for a case having no grid or boundary layer trip, yielding a nominally laminar boundary layer at the jet exit. This case illustrates the profound effect of the initial boundary layer state on the jet evolution and excitability. This jet decayed the fastest naturally, and consequently, it was the least excitable, in spite of very low initial turbulence intensity (0.15%).
    Type of Medium: Electronic Resource
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  • 2
    Electronic Resource
    Electronic Resource
    Springer
    Experiments in fluids 17 (1994), S. 415-426 
    ISSN: 1432-1114
    Source: Springer Online Journal Archives 1860-2000
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Notes: Abstract A modal spectrum technique was used to study coherent instability modes (both axisymmetric and azimuthal) triggered by naturally occurring disturbances in a circular jet. This technique was applied to a high Reynolds number (400,000) jet for both untripped (transitional) and tripped (turbulent) nozzle exit boundary layers, with both cases having a core turbulence level of 0.15%. The region up to the end of the potential core was dominated by the axisymmetric mode, with the azimuthal modes dominating further downstream. The growth of the azimuthal modes was observed closer to the nozzle exit for the jet with a transitional boundary layer. Whether for locally parallel flow or slowly diverging flow, even at low levels of acoustic forcing, the inviscid linear theory is seen to be inadequate for predicting the amplitude of the forced mode. In contrast, the energy integral approach reasonably predicts the evolution of the forced mode.
    Type of Medium: Electronic Resource
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  • 3
    Publication Date: 1994-10-01
    Print ISSN: 0723-4864
    Electronic ISSN: 1432-1114
    Topics: Mechanical Engineering, Materials Science, Production Engineering, Mining and Metallurgy, Traffic Engineering, Precision Mechanics
    Published by Springer
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  • 4
    Publication Date: 1989-07-01
    Print ISSN: 0899-8213
    Topics: Physics
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  • 5
    Publication Date: 2011-08-24
    Keywords: AERODYNAMICS
    Type: AIAA Journal (ISSN 0001-1452); 30; 6, Ju; 1482
    Format: text
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  • 6
    facet.materialart.
    Unknown
    In:  Other Sources
    Publication Date: 2011-08-24
    Description: Time-averaged and fluctuating quantities are measured in a free turbulent swirling jet. Data from a two-component laser Doppler anemometry (LDA) are compared to the measurements via hot-wire and 5-hole pitot probes. To acquire the proper seeding density near the axis of a swirling jet for LDA measurements proved difficult. This is due to an imbalance of the centrifugal force and radial pressure gradient, which throws the seeding material off the axis. Despite this problem, close agreement between various measurement techniques is obtained.
    Keywords: INSTRUMENTATION AND PHOTOGRAPHY
    Type: In: Laser anemometry - Advances and applications 1991; Proceedings of the 4th International Conference, Cleveland, OH, Aug. 5-9, 1991. Vol. 1 (A93-23776 08-35); p. 77-82.
    Format: text
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  • 7
    Publication Date: 2005-11-30
    Description: The principal suppressor parameters and their relationships have been used to formulate a suppressor design methodology which has been applied to the design of several full-scale suppressors. Tests of these suppressors on several full-scale fans have demonstrated noise reductions of the order of 10 PNdB. The amount of suppression in several instances seems to have been limited by reaching noise floors that are not clearly at the estimated jet noise level but are not far above it. In addition to identifying noise floors, two other areas are considered. The first is attenuation by the fan exhaust suppressors, which seems in most cases to be less than that of the inlet. The second is the effectiveness of outer cowl treatment alone on multiple pure tones. This question relates to whether a high-speed fan can become as quiet as a low-speed fan without a substantial increase in the amount of treatment.
    Keywords: AIRCRAFT
    Type: Aircraft Engine Noise Reduction; p 63-102
    Format: text
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  • 8
    Publication Date: 2006-07-16
    Description: The turbofan engine's noise-producing components are discussed in terms of efficient and economical noise reduction techniques that do not penalize the engine performance or weight significantly. Specific topics covered include fan noise, acoustic suppression, jet noise technology, combustor noise, and aircraft noise prediction.
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Aeropropulsion 1979; p 85-128
    Format: text
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  • 9
    Publication Date: 2006-04-20
    Description: Sources and characteristics of aircraft noise for conventional and V/STOL aircraft
    Keywords: AIRCRAFT
    Type: AIRCRAFT PROPULSION 1971; P 169-210
    Format: text
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  • 10
    Publication Date: 2011-08-18
    Description: An equation for acoustic ray paths in a spatially varying mean flow has been examined to determine some of the characteristics of the flow gradient effects on sound propagation. In a potential flow the acoustic rays are deflected in the direction of increasing mean flow, and the gradient of the mean flow speed is the dominant factor causing the ray deflection. In contrast, in a sheared mean flow, the vorticity is the dominant factor in deflection of the acoustic rays.
    Keywords: ACOUSTICS
    Type: Acoustical Society of America; vol. 70
    Format: text
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