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    Jet Surface Interaction Test: Far Field Noise Results

    Source: Journal of Engineering for Gas Turbines and Power:;2013:;volume( 135 ):;issue: 007::page 71201
    Author:
    Brown, Clifford A.
    DOI: 10.1115/1.4023605
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: Many configurations proposed for the next generation of aircraft rely on the wing or other aircraft surfaces to shield the engine noise from the observers on the ground. However, the ability to predict the shielding effect and any new noise sources that arise from the highspeed jet flow interacting with a hard surface is currently limited. Furthermore, quality experimental data from jets with surfaces nearby suitable for developing and validating noise prediction methods are usually tied to a particular vehicle concept and, therefore, very complicated. The JetSurface Interaction Tests are intended to supply a high quality set of data covering a wide range of surface geometries and positions and jet flows to researchers developing aircraft noise prediction tools. The initial goal is to measure the noise of a jet near a simple planar surface while varying the surface length and location in order to: (1) validate noise prediction schemes when the surface is acting only as a jet noise shield and when the jetsurface interaction is creating additional noise, and (2) determine regions of interest for future, more detailed, tests. To meet these objectives, a flat plate was mounted on a twoaxis traverse in two distinct configurations: (1) as a shield between the jet and the observer and (2) as a reflecting surface on the opposite side of the jet from the observer. The surface length was varied between 2 and 20 jet diameters downstream of the nozzle exit. Similarly, the radial distance from the jet centerline to the surface face was varied between 1 and 16 jet diameters. Farfield and phased array noise data were acquired at each combination of surface length and radial location using two nozzles operating at jet exit conditions across several flow regimes: subsonic cold, subsonic hot, underexpanded, ideally expanded, and overexpanded supersonic. The farfield noise results, discussed here, show where the jet noise is partially shielded by the surface and where jetsurface interaction noise dominates the low frequency spectrum as a surface extends downstream and approaches the jet plume.
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      Jet Surface Interaction Test: Far Field Noise Results

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    contributor authorBrown, Clifford A.
    date accessioned2017-05-09T00:58:19Z
    date available2017-05-09T00:58:19Z
    date issued2013
    identifier issn1528-8919
    identifier othergtp_135_7_071201.pdf
    identifier urihttp://yetl.yabesh.ir/yetl/handle/yetl/151636
    description abstractMany configurations proposed for the next generation of aircraft rely on the wing or other aircraft surfaces to shield the engine noise from the observers on the ground. However, the ability to predict the shielding effect and any new noise sources that arise from the highspeed jet flow interacting with a hard surface is currently limited. Furthermore, quality experimental data from jets with surfaces nearby suitable for developing and validating noise prediction methods are usually tied to a particular vehicle concept and, therefore, very complicated. The JetSurface Interaction Tests are intended to supply a high quality set of data covering a wide range of surface geometries and positions and jet flows to researchers developing aircraft noise prediction tools. The initial goal is to measure the noise of a jet near a simple planar surface while varying the surface length and location in order to: (1) validate noise prediction schemes when the surface is acting only as a jet noise shield and when the jetsurface interaction is creating additional noise, and (2) determine regions of interest for future, more detailed, tests. To meet these objectives, a flat plate was mounted on a twoaxis traverse in two distinct configurations: (1) as a shield between the jet and the observer and (2) as a reflecting surface on the opposite side of the jet from the observer. The surface length was varied between 2 and 20 jet diameters downstream of the nozzle exit. Similarly, the radial distance from the jet centerline to the surface face was varied between 1 and 16 jet diameters. Farfield and phased array noise data were acquired at each combination of surface length and radial location using two nozzles operating at jet exit conditions across several flow regimes: subsonic cold, subsonic hot, underexpanded, ideally expanded, and overexpanded supersonic. The farfield noise results, discussed here, show where the jet noise is partially shielded by the surface and where jetsurface interaction noise dominates the low frequency spectrum as a surface extends downstream and approaches the jet plume.
    publisherThe American Society of Mechanical Engineers (ASME)
    titleJet Surface Interaction Test: Far Field Noise Results
    typeJournal Paper
    journal volume135
    journal issue7
    journal titleJournal of Engineering for Gas Turbines and Power
    identifier doi10.1115/1.4023605
    journal fristpage71201
    journal lastpage71201
    identifier eissn0742-4795
    treeJournal of Engineering for Gas Turbines and Power:;2013:;volume( 135 ):;issue: 007
    contenttypeFulltext
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    DSpace software copyright © 2002-2015  DuraSpace
    نرم افزار کتابخانه دیجیتال "دی اسپیس" فارسی شده توسط یابش برای کتابخانه های ایرانی | تماس با یابش
    yabeshDSpacePersian