Flow Separation Associated with 3-D Shock-Boundary Layer Interaction (SBLI)

Morajkar, Rohan R.; Klomparens, Robin; Eagle, W. Ethan; Driscoll, James F.; Gamba, Mirko

doi:10.2514/6.2014-1138

Cited by 7 publications

(15 citation statements)

References 18 publications

(14 reference statements)

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“…Note that the definition of solid-body rotation vorticity ω RR [Eq. (6)] is similar to that of vorticity ω [Eq. 3], but vorticity is defined directly from ∇u (through Ω), whereas rigid-body rotation vorticity is defined from ∇u after the pure shear component is separated from it using the TDM method (i.e, fromΩ).…”

Section: Planar Surrogate Of Triple Decomposition Of Motionmentioning

confidence: 90%

“…Qualitative evidence was provided by surface oilflow and wall pressure data by Reda and Murphy [11] and Bruce et al [12]. Recently, Eagle and Driscoll [4], Eagle [5], and Morajkar et al [6] used stereo-PIV to record a comprehensive database that included the three components of velocity along 25 orthogonal measurement planes. However, there have been no attempts to determine the actual locations where separation begins and the relative sizes of the sidewall and bottom-wall regions.…”

Section: Previous Researchmentioning

confidence: 99%

“…This work builds on and differentiates from that previous work to further assess and verify the structure of the flow and the separated regions using conditional statistics on the velocity field and TDM. The work is based on the database first constructed for this flow configuration [5] and later extended to include more measurement planes [6].…”

mentioning

confidence: 99%

“…There are many examples of flow separation for which the velocity field is intermittent and highly unsteady [1,2,[4][5][6]. It is not surprising that Reynolds-averaged Navier-Stokes computations of these examples show poor agreement with experiments [8].…”

mentioning

confidence: 99%

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Relationship Between Intermittent Separation and Vortex Structure in a Three-Dimensional Shock/Boundary-Layer Interaction

et al. 2016

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Section: Planar Surrogate Of Triple Decomposition Of Motionmentioning

confidence: 90%

Section: Previous Researchmentioning

confidence: 99%

mentioning

confidence: 99%

mentioning

confidence: 99%

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Relationship Between Intermittent Separation and Vortex Structure in a Three-Dimensional Shock/Boundary-Layer Interaction

et al. 2016

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“…Measurements on transverse vertical (TV) planes are performed on the lower right corner (as one looks downstream) of the duct cross-section at three streamwise direction: (TV1) -100 mm, (TV2) -50 mm and (TV3) 75 mm with respect to the location where we have positioned the leading edge of a shock generator in our previous work [27,3].…”

Section: B Stereo Particle Image Velocimetry (Spiv)mentioning

confidence: 99%

Turbulence characteristics of supersonic corner flows in a low aspect ratio rectangular channel

Morajkar

Gamba

2016

54th AIAA Aerospace Sciences Meeting

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Shock-Induced Separation and Control in a 4.32-Aspect-Ratio Test Section

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Lambert,

McQuilling

et al. 2024

Journal of Propulsion and Power

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Experimental test sections studying shock-wave–boundary-layer interactions are usually right-angled by design to replicate the supersonic engine inlets where these interactions are observed. To avoid flow separation and shock effects on the side walls, investigations are typically performed on the centerline of the test section. However, the centerlines of small-aspect-ratio test sections can be significantly affected by the flow structures generated in the corners. Results using a large-aspect-ratio test section at a freestream Mach number of 1.6 include centerline and corner flow separation topologies, schlieren images of shock structures, total pressure profiles, and surface static pressures throughout the interaction region. These results provide evidence that the large-aspect-ratio test section can produce a large area of centerline flow that is unaffected by the separation and shock structures generated in the corners, which is a significant improvement over most of the smaller-aspect-ratio test sections employed for these types of studies. Microvortex generators are also employed upstream of the interaction, and measurements indicate a five-vortex system that energizes the near-wall boundary layer enough to overcome the shock’s adverse pressure gradient while remaining attached.

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Flow Separation Associated with 3-D Shock-Boundary Layer Interaction (SBLI)

Cited by 7 publications

References 18 publications

Relationship Between Intermittent Separation and Vortex Structure in a Three-Dimensional Shock/Boundary-Layer Interaction

Relationship Between Intermittent Separation and Vortex Structure in a Three-Dimensional Shock/Boundary-Layer Interaction

Turbulence characteristics of supersonic corner flows in a low aspect ratio rectangular channel

Shock-Induced Separation and Control in a 4.32-Aspect-Ratio Test Section

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