Experimental Study of Unswept and Swept Oblique Shock-Turbulent Boundary Layer Interactions

Hainsworth, J. M.; Dawson, Robyn; Little, Jesse

doi:10.2514/6.2014-2738

Cited by 6 publications

(4 citation statements)

References 16 publications

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“…In the previous study, Hainsworth et al found the same type of 3D flow within a 2D interaction, though their analysis showed a different spanwise trend amongst the boundary layers. 22 While further research is necessary to investigate this three-dimensionality, there is enough evidence to conclude that 3D flow features are not limited solely to the 40 degree wedge or conical interactions. Nevertheless, it will be shown that these 3D trends are significantly stronger in conical interactions.…”

Section: Boundary Layer Profiles Within the Interactionmentioning

confidence: 97%

“…This discrepancy was investigated in our previous work and those efforts have been expanded upon here. 22 The objective of this work is to bridge the gap between 2D and 3D SBLIs through experimental investigation of the effect of sweep on the interaction between an impinging oblique shocks and turbulent boundary layers. In contrast to other swept interactions (e.g.…”

Section: Introductionmentioning

confidence: 99%

“…This work is a continuation of previous research in which impinging oblique shocks were studied using a 15 degree wedge swept at 0, 22.5 and 40 degrees for Mach 2.3. 22 The previous work was concerned mainly with interaction lengths extracted from mean flow data. That study found that interaction length decreased with increasing sweep angle and that the 40 degree swept interaction displayed conical similarity while the unswept and 22.5 degree swept interactions showed cylindrical similarity.…”

Section: Introductionmentioning

confidence: 99%

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Effects of Sweep on Impinging Oblique Shock-Turbulent Boundary Layer Interaction

Dawson-Ruiz

Pederson

Little

2015

45th AIAA Fluid Dynamics Conference

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The characteristics of unswept and swept impinging oblique shock turbulent boundary layer interaction (SBLI) are examined with stereoscopic particle image velocimetry (PIV). This is a continuation of a previous study in which an impinging shock is produced by a 15 degree wedge that is swept at angles of 0, 22.5, and 40 degrees in Mach 2.3 flow. The SBLI is investigated at three spanwise planes. The interaction length is found to decrease with increasing sweep angle across the test matrix. The 22.5 degree and unswept case have cylindrical similarity and the 40 degree interaction appears conical. The present study also includes a mirrored 40 degree wedge which shows that the previous results are not due to a particular sidewall boundary layer. All cases show separated flow in the interaction region and most contain reverse flow that is clearly outside of the measurement uncertainty. Results are compared against literature for swept impinging shocks and compression ramps. Nomenclature u = streamwise velocity U ∞ = free stream velocity M ∞ = free stream Mach number δ = boundary layer thickness (99% of U ∞ ) δ * = displacement thickness (incompressible) θ = momentum thickness (incompressible) H = incompressible shape factor u τ = friction velocity P o = stagnation pressure T o = stagnation temperature Re θ = Reynolds number based on momentum thickness ε L = bias error in the interaction length ε fy = bias error in the measured y-position of the floor L = streamwise SBLI region length, X r -X i X r = streamwise projected reflected shock impingement point X i = streamwise projected primary inviscid shock impingement point in a given plane i x = streamwise coordinate x i * = normalized streamwise coordinate, (x-X o )/L in a given plane i y f = measured y-position of the floor z = normalized global spanwise position, z dim /(wedge span), measured from start of interaction

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Section: Boundary Layer Profiles Within the Interactionmentioning

confidence: 97%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

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Effects of Sweep on Impinging Oblique Shock-Turbulent Boundary Layer Interaction

Dawson-Ruiz

Pederson

Little

2015

45th AIAA Fluid Dynamics Conference

Self Cite

View full text Add to dashboard Cite

show abstract

“…The symmetry of an SBLI is often exploited by experimentalists in order to develop experimental techniques that can provide useful results. Hainsworth et al 10 exploited the conical symmetry of a swept wedge SBLI in order to obtain some 3D information about the flow. In their study, planar PIV was performed at different planes along the shock wave in order to determine the change in the interaction features at various spanwise distances.…”

Section: Introductionmentioning

confidence: 99%

Volumetric Measurement of a Shock Wave-Turbulent Boundary Layer Interaction Using Plenoptic Particle Image Velocimetry

Bolton

Thurow

Alvi³

et al. 2016

32nd AIAA Aerodynamic Measurement Technology and Ground Testing Conference

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This paper explores the application of Plenoptic Particle Image Velocimetry (PIV) to study a Shock Wave-Turbulent Boundary Layer Interaction (SBLI) induced by an unswept fin. The fin is placed in a Mach 2 flow at an angle of attack of 15 •. The oblique shock wave introduced by the fin interacts with the turbulent boundary layer along the bottom wall. A plenoptic camera is a unique diagnostic tool that captures 3D information using a single camera. This novel imaging system can be combined with particle image velocimetry to obtain 3D velocity data about a flow field. For comparison, the volume analyzed in this study relates to a previous study in the same facility using two planar PIV experiments separated by approximately 12 mm. This is the first application of a plenoptic camera for volumetric studies of SBLI, and it has proven the unique capabilities of the plenoptic camera to obtain 3D velocity information in areas of limited optical access and in supersonic flows. Comparison with previous planar PIV shows the same interaction structure present in both results.

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Single Camera 3D Measurement of a Shock Wave-Turbulent Boundary Layer Interaction

Bolton

Thurow

Alvi³

et al. 2017

55th AIAA Aerospace Sciences Meeting

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Experimental Study of Unswept and Swept Oblique Shock-Turbulent Boundary Layer Interactions

Cited by 6 publications

References 16 publications

Effects of Sweep on Impinging Oblique Shock-Turbulent Boundary Layer Interaction

Effects of Sweep on Impinging Oblique Shock-Turbulent Boundary Layer Interaction

Volumetric Measurement of a Shock Wave-Turbulent Boundary Layer Interaction Using Plenoptic Particle Image Velocimetry

Single Camera 3D Measurement of a Shock Wave-Turbulent Boundary Layer Interaction

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