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    Flow Separation in Shock Wave Boundary Layer Interactions

    Source: Journal of Engineering for Gas Turbines and Power:;1994:;volume( 116 ):;issue: 001::page 98
    Author:
    A. Hamed
    ,
    A. Kumar
    DOI: 10.1115/1.2906816
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: This work presents an assessment of the experimental data on separated flow in shock wave turbulent boundary layer interactions at hypersonic and supersonic speeds. The data base consists of selected configurations where the only characteristic length in the iteration is the incoming boundary layer thickness. It consists of two-dimensional and axisymmetric interactions in compression corners or cylinder-flares, and externally generated oblique shock interactions with boundary layers over flat plates or cylindrical surfaces. The conditions leading to flow separation and the empirical correlations for incipient separation are reviewed. The effects of Mach number, Reynolds number, surface cooling, and the methods of detecting separation are discussed.
    keyword(s): Shock waves , Boundary layers , Flow separation , Separation (Technology) , Thickness , Flow (Dynamics) , Mach number , Cooling , Boundary layer turbulence , Compression , Cylinders , Databases , Flat plates , Reynolds number , Shock (Mechanics) AND Corners (Structural elements) ,
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      Flow Separation in Shock Wave Boundary Layer Interactions

    URI
    http://yetl.yabesh.ir/yetl1/handle/yetl/113614
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    • Journal of Engineering for Gas Turbines and Power

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    contributor authorA. Hamed
    contributor authorA. Kumar
    date accessioned2017-05-08T23:44:15Z
    date available2017-05-08T23:44:15Z
    date copyrightJanuary, 1994
    date issued1994
    identifier issn1528-8919
    identifier otherJETPEZ-26722#98_1.pdf
    identifier urihttp://yetl.yabesh.ir/yetl/handle/yetl/113614
    description abstractThis work presents an assessment of the experimental data on separated flow in shock wave turbulent boundary layer interactions at hypersonic and supersonic speeds. The data base consists of selected configurations where the only characteristic length in the iteration is the incoming boundary layer thickness. It consists of two-dimensional and axisymmetric interactions in compression corners or cylinder-flares, and externally generated oblique shock interactions with boundary layers over flat plates or cylindrical surfaces. The conditions leading to flow separation and the empirical correlations for incipient separation are reviewed. The effects of Mach number, Reynolds number, surface cooling, and the methods of detecting separation are discussed.
    publisherThe American Society of Mechanical Engineers (ASME)
    titleFlow Separation in Shock Wave Boundary Layer Interactions
    typeJournal Paper
    journal volume116
    journal issue1
    journal titleJournal of Engineering for Gas Turbines and Power
    identifier doi10.1115/1.2906816
    journal fristpage98
    journal lastpage103
    identifier eissn0742-4795
    keywordsShock waves
    keywordsBoundary layers
    keywordsFlow separation
    keywordsSeparation (Technology)
    keywordsThickness
    keywordsFlow (Dynamics)
    keywordsMach number
    keywordsCooling
    keywordsBoundary layer turbulence
    keywordsCompression
    keywordsCylinders
    keywordsDatabases
    keywordsFlat plates
    keywordsReynolds number
    keywordsShock (Mechanics) AND Corners (Structural elements)
    treeJournal of Engineering for Gas Turbines and Power:;1994:;volume( 116 ):;issue: 001
    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
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