Control of forced shock-wave oscillations and separated boundary layer interaction

Galli, Arnaud; Corbel, Bernard; Bur, Reynald

doi:10.1016/j.ast.2005.07.008

Cited by 24 publications

(13 citation statements)

References 10 publications

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“…The research status in this field also indicates that the vane-type VG shapes are superior in performance when compared to the ramp/wedge-type VGs and, therefore, more innovative designs need to be looked into to match the effectiveness of the former. Although nothing concrete could be ascertained about control location, a rough estimate indicates that this distance is to be somewhere between (15)(16)(17)(18)(19)(20)(21)(22)(23)(24)(25)(26)(27)(28)(29)(30) x/ h (where x is the distance of the control location from the interaction).…”

Section: Thematic Issue On Supersonic Flow Controlmentioning

confidence: 99%

“…In particular, frequency forcing close to the natural shedding frequency reduced separation, while the latter increased at high frequency (corresponding to an acoustic-mode operation of the jet). Passive and active (by suction) techniques for the control of shock wave oscillations and separated boundary layer interaction in a transonic channel flow were investigated by Galli et al [23] who showed that passive control had no effect on shock unsteadiness. LES simulations of Franck and Colonius [24] confirmed a slight loss of control effectiveness when comparing the results for the same control parameters at low Mach numbers.…”

Section: Introductionmentioning

confidence: 99%

See 1 more Smart Citation

Supersonic flow control

Verma

Hadjadj

2015

Shock Waves

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Section: Thematic Issue On Supersonic Flow Controlmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Supersonic flow control

Verma

Hadjadj

2015

Shock Waves

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“…A number of experimental and numerical studies [2,3,[5][6][7][8] have implemented a variable geometry second throat to investigate the effects of downstream periodic pressure perturbations on shocks both experimentally and numerically. The authors of these studies found that the amplitude of shock motion decreased with increasing frequency (see Fig.…”

Section: Fmentioning

confidence: 99%

“…The maximum shock speed observed in experiments was 9 ms 1 , which implies that the shock could potentially move a streamwise distance of up to 1.1 mm during an exposure. Hence, it is estimated that shock position in a [7], b) Ott et al [2], and c) Edwards and Squire [6].…”

Section: A Experimentsmentioning

confidence: 99%

Experimental and Numerical Study of Oscillating Transonic Shock Waves in Ducts

Bruce¹,

Babinsky²,

Tartinville³

et al. 2011

AIAA Journal

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.J050944An experimental and computational study of a M 1 1:4 transonic shock wave in a parallel-walled duct subject to downstream pressure perturbations in the frequency range of 16-90 Hz has been conducted. The dynamics of unsteady shock motion and aspects of the unsteady transonic shock and turbulent tunnel-floor boundary-layer interaction have been investigated. The numerical computations were performed using an unsteady Reynoldsaveraged Navier-Stokes scheme. It is found that the (experimentally measured) shock dynamics are generally well replicated by the numerical scheme, especially at relatively low (40 Hz) frequencies. However, variations in shock/ boundary-layer interaction structure during unsteady shock motion observed in experiments are not always well predicted by the simulation. Significantly, the computations predict variations in shock/boundary-layer interaction size due to shock motion that are much larger and in the opposite sense to the variations observed in experiments.Comparison of the unsteady results from the present study with steady (experimental) results from the literature suggests that unsteady Reynolds-averaged Navier-Stokes code used in the present study models the unsteady shock/ boundary-layer interaction behavior as quasi-steady, whereas experiments suggest that it is more genuinely unsteady. Further work developing numerical methods that demonstrate a more realistic sensitivity of shock/ boundary-layer interaction structure to unsteady shock motion is required.

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“…Recently, comprehensive study on the advances of SBLI with emphasis on ow unsteadiness, heat transfer prediction, multi-shock boundary-layer interaction, and ow control techniques has been performed [25]. Other recent studies have been carried out on unsteadiness of SBLI [26,27] and control methods such as bleed, vortex generator, and micro actuators [28][29][30]. Also, some recent experiments and theoretical e orts have been made to investigate the e ect of ow control methods such as bleed on SBLI for supersonic and hypersonic inlets [31][32][33][34][35].…”

Section: Introductionmentioning

confidence: 99%

Effects of Shock Wave/Boundary-Layer Interaction on Performance and Stability of a Mixed-Compression Inlet

Soltani¹,

Daliri²,

Sepahi-Younsi³

2016

Scientia Iranica

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Abstract. Experiments were conducted to study various kinds of Shock wave/BoundaryLayer Interaction (SBLI) in an axisymmetric mixed-compression inlet. Experimental ndings were compared and veri ed by numerical solutions where possible. Di erent types of SBLI relevant to the mixed-compression inlets are classi ed. Interactions of normal shock wave/boundary-layer at subcritical condition and in buzz condition are investigated using Schlieren and shadowgraph ow visualization as well as unsteady pressure recordings. The data is compared with the CFD predictions. Interactions of cowl lip re ected oblique shock and the terminal normal shock with the spike boundary-layer at both critical and supercritical operations, which lead to pseudo-shock phenomena, are also studied. Experimental pressure recordings are used for validation and discussion. For near-critical throttling values, interaction of internal compression oblique shocks with boundary-layer and pseudo-shock phenomenon is dominant. Formation of lambda shock due to interaction of separated boundary-layer with normal shock wave is investigated. Each type of ow interaction phenomena has di erent e ects on the stability and performance of the inlet. Interaction of terminal normal shock with internal duct boundary-layer causes pseudoshock phenomenon that increases ow distortion and reduces total pressure recovery. Interaction of normal shock with cone boundary-layer causes buzz instability and degrades inlet performance.

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Control of forced shock-wave oscillations and separated boundary layer interaction

Cited by 24 publications

References 10 publications

Supersonic flow control

Supersonic flow control

Experimental and Numerical Study of Oscillating Transonic Shock Waves in Ducts

Effects of Shock Wave/Boundary-Layer Interaction on Performance and Stability of a Mixed-Compression Inlet

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