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    Shock–Boundary Layer-Interaction Control Through Recirculation in a Hypersonic Inlet

    Source: Journal of Fluids Engineering:;2020:;volume( 142 ):;issue: 011::page 0114502-1
    Author:
    Ruban, Alex
    ,
    Menezes, Viren
    ,
    Balasubramanian, Sridhar
    ,
    Srinivasan, K.
    DOI: 10.1115/1.4048141
    Publisher: The American Society of Mechanical Engineers (ASME)
    Abstract: This technical brief presents a flow separation mitigation device, called cavity-recirculator that can be used to control flow separation during shock wave–boundary layer interaction (SBLI) in high-speed intake flows. The cavity-recirculator isolates the flow separation bubble generated at the SBLI spot, thereby thinning the boundary layer and reducing the blockage of the inviscid stream in the duct. The device has a potential application in scramjet engine intakes/isolators. The cavity-recirculator was tested on a single-ramp-compression intake model in a hypersonic shock tunnel, in a freestream of Mach 8 (±0.1). The device operation and effectiveness were assessed by flow visualization and pressure measurements in the test model. The measurements and visualization displayed a mitigation of flow separation through an improved flow field with a single shock train and the absence of flow separation shock, in the inlet.
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      Shock–Boundary Layer-Interaction Control Through Recirculation in a Hypersonic Inlet

    URI
    http://yetl.yabesh.ir/yetl1/handle/yetl/4274644
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    • Journal of Fluids Engineering

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    contributor authorRuban, Alex
    contributor authorMenezes, Viren
    contributor authorBalasubramanian, Sridhar
    contributor authorSrinivasan, K.
    date accessioned2022-02-04T21:58:54Z
    date available2022-02-04T21:58:54Z
    date copyright9/4/2020 12:00:00 AM
    date issued2020
    identifier issn0098-2202
    identifier otherfe_142_11_111211.pdf
    identifier urihttp://yetl.yabesh.ir/yetl1/handle/yetl/4274644
    description abstractThis technical brief presents a flow separation mitigation device, called cavity-recirculator that can be used to control flow separation during shock wave–boundary layer interaction (SBLI) in high-speed intake flows. The cavity-recirculator isolates the flow separation bubble generated at the SBLI spot, thereby thinning the boundary layer and reducing the blockage of the inviscid stream in the duct. The device has a potential application in scramjet engine intakes/isolators. The cavity-recirculator was tested on a single-ramp-compression intake model in a hypersonic shock tunnel, in a freestream of Mach 8 (±0.1). The device operation and effectiveness were assessed by flow visualization and pressure measurements in the test model. The measurements and visualization displayed a mitigation of flow separation through an improved flow field with a single shock train and the absence of flow separation shock, in the inlet.
    publisherThe American Society of Mechanical Engineers (ASME)
    titleShock–Boundary Layer-Interaction Control Through Recirculation in a Hypersonic Inlet
    typeJournal Paper
    journal volume142
    journal issue11
    journal titleJournal of Fluids Engineering
    identifier doi10.1115/1.4048141
    journal fristpage0114502-1
    journal lastpage0114502-8
    page8
    treeJournal of Fluids Engineering:;2020:;volume( 142 ):;issue: 011
    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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