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  • 1
    Publication Date: 2006-10-26
    Description: Atmospheric effects on sonic boom pressure signatures
    Keywords: METEOROLOGY
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  • 2
    Publication Date: 2013-08-31
    Description: Nonlinear method for predicting acoustic properties of thin porous sheets
    Keywords: PHYSICS, GENERAL
    Type: PROGR. OF NASA RES. RELATING TO NOISE ALLEVIATION OF LARGE SUBSONIC JET AIRCRAFT 1968; P 17-27
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  • 3
    Publication Date: 2011-08-18
    Description: Three methods for measuring the acoustic properties of bulk materials have been evaluated. The methods differ from one another in their practical implementation and reliability. The two more convenient methods exploit changes in surface impedance of test samples resulting from a change in the test sample geometry or boundary conditions. The results from these surface methods are compared with that obtained using Scott's method. In Scott's method the propagation constant is obtained by a 'direct' measurement inside the test material by means of a probe tube. The comparisons suggest that the surface methods will provide reliable and accurate results when the test sample behaves as a rigid porous structure.
    Keywords: ACOUSTICS
    Type: Acoustical Society of America, Journal (ISSN 0001-4966); 74; 1577-158
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  • 4
    Publication Date: 2011-08-18
    Description: Previously cited in issue 10, p. 1378, Accession no. A83-25963
    Keywords: AIRCRAFT PROPULSION AND POWER
    Type: Journal of Aircraft (ISSN 0021-8669); 21; 491-497
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  • 5
    Publication Date: 2019-05-21
    Description: Atmospheric effects on sonic boom pressure wave shapes
    Keywords: PHYSICS, GENERAL
    Type: NASA-RP-79
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  • 6
    Publication Date: 2019-05-21
    Description: Measurements of shock wave overpressures from airplanes at altitudes to 75,000 feet & supersonic speed
    Keywords: BIOSCIENCES
    Type: NASA-TN-D-2021
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  • 7
    Publication Date: 2019-06-28
    Description: The responses of a hot film sensor and a pressure probe to acoustic excitation in steady flow up to a Mach number of 0.5 were measured and compared with the responses of a microphone, flush mounted in the wall of the flow duct. When compared in terms of fluctuating pressure, the response of the pressure probe was less than that of the wall microphone by about 2.1 dB or less at the 0.5 Mach number, while the response of the ho film probe was as much as 6.0 dB above that of the wall sensor, at the Mach numbers 0.3 and 0.5. In terms of fluctuating Reynolds number, the response of the hot film probe was greater than that of the wall-mounted sensor by at most 5.0 dB at the same Mach numbers. Removing the response contribution from fluctuating temperature in the hot film mathematical model improved the agreement between the two transducer responses for both comparisons.
    Keywords: FLUID MECHANICS AND HEAT TRANSFER
    Type: AIAA PAPER 86-1889
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  • 8
    Publication Date: 2019-06-28
    Description: Flight experiments are being conducted with the objective to investigate the interactions between acoustic disturbances and laminar flow in the flight environment. In the experiments, the laminar boundary layer on the nacelles will be exposed to discrete and broadband external noises, and the effect of varying noise levels and frequencies on the stability of the laminar flow will be studied. The present paper provides an overview of the complete project and a status report on the results which have been obtained. The flight experiment is conducted with the aid of a modified research aircraft. The phase I flight tests are concerned with a quick and simple determination of natural laminar flow (NLF) behavior on an engine nacelle. Attention is given to instrumentation, the acoustic noise source, flow visualization, and the test results.
    Keywords: AIRCRAFT DESIGN, TESTING AND PERFORMANCE
    Type: AIAA PAPER 86-9756
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  • 9
    Publication Date: 2019-06-28
    Description: An experiment was conducted to compare the relative responses of a hot-film probe and a pressure probe positioned in a flow duct carrying mean flow and progressive acoustic waves. The response of each probe was compared with that of a condenser-type microphone flush mounted in the duct wall for flow Mach numbers up to about 0.5. The response of the pressure probe was less than that of the flush-mounted microphone by not more than about 2.1 dB at the highest centerline Mach number. This decreased response of the probe can likely be attributed to flow-induced impedance changes at the probe sensor orifices. The response of the hot-film probe, expressed in terms of fluctuating pressure, was greater than that of the flush-mounted microphone by as much as 6.0 dB at the two higher centerline Mach numbers. Removal of the contribution from fluctuating temperature in the hot-film analytical model greatly improved the agreement between the two transducer responses.
    Keywords: ACOUSTICS
    Type: NASA-TP-2581 , L-16079 , NAS 1.60:2581
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  • 10
    Publication Date: 2019-06-28
    Description: The acoustic response of a semireverberant enclosure with two interacting, velocity-prescribed source distributions was analyzed using standard modal analysis techniques with a view toward a better understanding of active noise control. Different source and enclosure dimensions, source separations, and single-wall admittances were studied over representative frequency bandwidths of 10 Hz with source relative phase as a parameter. Results indicate that power radiated into the enclosure agree qualitatively with the spatial average of the mean square pressure, even though the reverberant field is nondiffuse. Decreases in acoustic power can therefore be used to estimate global noise reduction in a nondiffuse semireverberant environment. As might be expected, parametric studies indicate that maximum power reductions of up to 25 dB can be achieved when secondary and primary sources are compact and closely spaced. Although less success is achieved with increasing frequency and source separation or size, significant suppression of up to 8 dB still occurs over the 1 to 2 Hz bandwidth.
    Keywords: ACOUSTICS
    Type: NASA-TP-2472 , L-15944 , NAS 1.60:2472
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