SBLI control for wings and inlets

Babinsky, Holger; Ogawa, H.

doi:10.1007/978-3-540-85168-4_7

Cited by 14 publications

(16 citation statements)

References 20 publications

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“…A SHOCK/BOUNDARY-LAYER interaction (SBLI) flow control technique proposed recently is to distribute an array of micro vortex generators (MVGs), whose height is less than the boundary layer thickness, ahead of the region with adverse flow conditions. [1][2][3][4][5][6][7][8][9][10][11][12][13][14][15][16][17][18] These MVGs are thought to function similarly to conventional vortex generators in energizing the boundary layer via entrainment of the freestream flow by trailing vortices. The main difference between MVGs and conventional vortex generators is that the former produces less drag.…”

Section: Introductionmentioning

confidence: 99%

Experimental and Numerical Study of Flow Topology Past Micro-Vortex Generators

Pierce

Shih

et al. 2010

40th Fluid Dynamics Conference and Exhibit

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Detailed experimental and numerical visualizations of the flow past a micro vortex generator (MVG) in the form of a ramp with swept sides in a Mach 2.5 flow revealed a complex near-field topology. The incoming flow separated over the leading edge of the MVG despite the ramp angle being below the threshold for incipient separation. The separation over the MVG protuberance produced a weak trailing horseshoe vortex system. The attachment line shows a saddle/foci combination on each side of a nodal point of attachment. The flow over the top of the MVG separated off the slant edges to produce a large primary vortex pair. This large primary vortex pair induced two secondary vortex filament pairs, one off the top of the MVG and another at the corner of the MVG with the flat plate. Extra complexities were revealed at the trailing edge with at least two pairs of saddle/foci combinations observed. It is postulated that vortex filaments spring from the various saddle/foci combinations as these were not observed experimentally or computationally. Symmetry breaking due to flow unsteadiness was also observed in the MVG wake.

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Section: Introductionmentioning

confidence: 99%

Experimental and Numerical Study of Flow Topology Past Micro-Vortex Generators

Pierce

Shih

et al. 2010

40th Fluid Dynamics Conference and Exhibit

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“…Figure 1(c) shows a range of SWBLI types occurring within a supersonic compression inlet (e.g. figure 1a,b), which is one of the most commonly studied applications (Longley & Greitzer 1992;Smart 2001;Ogawa & Babinsky 2006;Babinsky & Ogawa 2008;Babinsky, Oorebeek & Cottingham 2013;Loth et al 2013).…”

mentioning

confidence: 99%

Confinement effects on regular–irregular transition in shock-wave–boundary-layer interactions

Grossman

Bruce

2018

J. Fluid Mech.

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An oblique shock wave is generated in a Mach 2 flow at a flow deflection angle of 12• . The resulting shock-wave-boundary-layer interaction (SWBLI) at the tunnel wall is observed. A novel traversable shock generator allows the position of the SWBLI to be varied relative to a downstream expansion fan. The relationship between the SWBLI, the expansion fan and the wind tunnel arrangement is studied. Schlieren photography, surface oil flow visualisation, particle image velocimetry and high-spatial-resolution wall pressure measurements are used to investigate the flow. It is observed that stream-normal movement of the shock generator downwards (towards the floor and hence the point of shock reflection) is accompanied by (1) growth in the streamwise extent of the shock-induced boundary layer separation, (2) upstream movement of the shock-induced separation point while the reattachment point remains nearly fixed, (3) an increase in separation shock strength and (4) transition between regular and irregular (Mach) reflection without an increase in incident shock strength. The role of free interaction theory in defining the separation shock angle is considered and shown to be consistent with the present measurements over a short streamwise extent. An SWBLI representation is proposed and reasoned which explains the apparent increase in separation shock strength that occurs without an increase in incident shock strength.

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“…To alleviate the unstart phenomena, VanWie et al (19) adopted flow injection. Babinsky et al (20)(21) demonstrated that, use of micro ramp vortex generators controls the boundary layer and leads to improvement in inlet performance. Numerical investigation to study the effect of bleed flow rate, bleed hole geometry is reported by Mizukami et al (22) , Syberg et al (23) and Vivek and Mittal (24) .…”

Section: Nomenclaturementioning

confidence: 99%

Starting characteristics of a rectangular supersonic air-intake with cowl deflection

Das¹,

Prasad²

2010

Aeronaut. j.

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CR contraction ratio (A t /A c ) h cIntake capture height L overall length of model m e mass flow rate at diffuser exit (kg/s) m i capture mass flow rate (kg/s) P static pressure P b back pressure P bs sustainable back pressure P i free stream pressure P 0e total pressure at exit P 0i total pressure of free stream PE pressure ratio at exit (P b /P i ) θ 1 first ramp angle θ 2 second ramp angle θ 3 first diffuser angle θ 4 second diffuser angle θ c cowl deflection angle x distance from leading edge Y distance along the height of intake Y max maximum intake exit height TH ratio of throttled area at exit and throat (A e /A t ) FD flow distortion PR pressure recovery ABSTRACT Experimental and computational investigations have been made to obtain the details of the flow field of a supersonic air-intake with different cowl deflection angles and back pressures at the exit. The flow field obtained with an inviscid computation on the basic configuration, designed for Mach 2·2, shows starting behaviour whereas computation with k-ω turbulence model and experiments indicate unstart characteristics. Both experiments and computations indicate that provision of a small angle at the cowl tip leads to start of the same intake and also improves it's performance. Results obtained with cowl deflection shows a better performance in comparison to performance achieved with a basic intake and with a bleed of 2·8%. Sustainable back pressure could be obtained through the computations made at different back pressures for different cowl deflection angles. Overall results suggest that provision of small cowl deflection angle itself leads to improvement in performance achieved in comparison to a bleed of 2·8%, even with back pressure at the exit. NOMENCLATUREA t throat area A c capture area A e exit area

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SBLI control for wings and inlets

Cited by 14 publications

References 20 publications

Experimental and Numerical Study of Flow Topology Past Micro-Vortex Generators

Experimental and Numerical Study of Flow Topology Past Micro-Vortex Generators

Confinement effects on regular–irregular transition in shock-wave–boundary-layer interactions

Starting characteristics of a rectangular supersonic air-intake with cowl deflection

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