Progress in shock wave/boundary layer interactions

Gaitonde, Datta V.

doi:10.1016/j.paerosci.2014.09.002

Cited by 521 publications

(140 citation statements)

References 180 publications

(215 reference statements)

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“…SBLI has been studied experimentally, theoretically, and numerically for more than 60 years. But it is still far from being solved and still needs more research work [1][2][3][4][5].…”

mentioning

confidence: 99%

Numerical Study on Wall Temperature Effects on Shock Wave/Turbulent Boundary-Layer Interaction

Zhu¹,

Yu²,

Tong

et al. 2017

AIAA Journal

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The effect of wall temperature on the size of the separation bubble in the shock wave/turbulent boundary-layer interaction of a 24 deg compression ramp with Mach 2.9 is numerically investigated. The ratios of wall temperature to recovery temperature T w ∕T r are 0.6, 1.14, 1.4, and 2.0, respectively. To validate the simulation, the statistical results with T w ∕T r 1.14 are tested and the results show a good agreement with theoretical and experimental results. It is shown that wall temperature has a remarkable effect on the size of the separation bubble and the size increases significantly with the increase of wall temperature. Through theoretical analysis, combined with numerical results, we get a semitheoretical formula L∕δ ∝ T w ∕T r 0.85 , in which L and δ are the length of the separation bubble and the thickness of upstream boundary layer, respectively. The turbulent kinetic energy budgets are also analyzed based on the numerical data, and results show that turbulence kinetic energy is chiefly produced both in the buffer layer and near the shock wave, and turbulent dissipation is mainly in the center of the separation bubble as well as in the nearwall region. It is also shown that the intrinsic compressibility effect is not significant in all these cases. = separation point δ = upstream boundary-layer thickness μ = viscosity coefficient ρ = density

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“…SBLI has been studied experimentally, theoretically, and numerically for more than 60 years. But it is still far from being solved and still needs more research work [1][2][3][4][5].…”

mentioning

confidence: 99%

Numerical Study on Wall Temperature Effects on Shock Wave/Turbulent Boundary-Layer Interaction

Zhu¹,

Yu²,

Tong

et al. 2017

AIAA Journal

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“…[1] Compared with some two-dimensional (2D) and quasi-threedimensional (q3D) SWTBLIs (i.e. those flows exhibiting homogeneity along the transverse direction, such as, a compression corner and/or an impinging oblique shock-wave/boundary layer interaction), the inhomogeneous fully three-dimensional (3D) SWTBLI problem is much less studied and understood [2] , although it occurs in real flow problems and has significant effects on the performances of supersonic aircraft inlets and control surfaces. Therefore, further research of 3D SWTBLI problems is of great importance in understanding their underlying flow physics and mechanisms, as well as improving the aerodynamic performance of systems in which these flows are present.…”

Section: Introductionmentioning

confidence: 99%

“…[2][3][4] In this flow configuration, a swept shock-wave is generated from the leading edge of a sharp semi-infinite single-fin and it interacts with a turbulent boundary layer developed along the flat plate. The shockwave is smeared when it penetrates into the viscous boundary layer and disturbs flow upstream and downstream of the inviscid shock-wave.…”

Section: Introductionmentioning

confidence: 99%

Investigation of Three-Dimensional Shock Wave/Turbulent-Boundary-Layer Interaction Initiated by a Single Fin

et al. 2017

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Investigation of three-dimensional shock wave/turbulent-boundary-layer interaction initiated by a single fin. AIAA Journal, 55 (2). pp. 509-523. ISSN 0001-1452 Available from: http://eprints.uwe.ac.uk/30142We recommend you cite the published version. The publisher's URL is: http://dx.doi.org/10.2514/1.J055283 Refereed: YesCopyright c 2016 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved. Disclaimer UWE has obtained warranties from all depositors as to their title in the material deposited and as to their right to deposit such material. UWE makes no representation or warranties of commercial utility, title, or fitness for a particular purpose or any other warranty, express or implied in respect of any material deposited. UWE makes no representation that the use of the materials will not infringe any patent, copyright, trademark or other property or proprietary rights. UWE accepts no liability for any infringement of intellectual property rights in any material deposited but will remove such material from public view pending investigation in the event of an allegation of any such infringement. PLEASE SCROLL DOWN FOR TEXT.

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“…SBLI occurs in all practical transonic, supersonic and hypersonic vehicles [18]. Especially normal shock-wave/ boundary-layer interaction (NSBLI) is a frequently occurring phenomenon that must be considered in supersonic inlet design [19].…”

Section: Introductionmentioning

confidence: 99%

Two and Three Dimensional Numerical Simulation of Supersonic Ramped Inlet

Askari

Soltani

2017

Scientia Iranica

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Two Dimensional (2D) and Three Dimensional (3D) numerical simulations of an external compression supersonic ramped inlet for a free stream Mach number of 2 are presented. Comparison between numerical results and experimental data showed that multi-block structured gird using standard k-ε turbulence model gives acceptable results. The diffuser shape was then gradually varied to a circular one to encompass the Aerodynamic Interface Plane (AIP). It is observed that the 3D simulation predicted a more accurate static pressure distribution during the length of supersonic inlet and total pressure distribution at the AIP in comparison with the 2D one. Further, a better estimation of Shock Boundary Layer Interaction (SBLI), shock structure, and turbulent flow is predicted by the 3D simulation. It seems that, even though the 2D simulation scheme is widely used, it is a very weak method with low accuracy while the 3D simulation is more accurate and gives detailed flow field. Therefore; for cases where a detailed flow study along with an accurate prediction of flow parameters as well as the shock structure are required, the 3D numerical simulation must be applied.

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Progress in shock wave/boundary layer interactions

Cited by 521 publications

References 180 publications

Numerical Study on Wall Temperature Effects on Shock Wave/Turbulent Boundary-Layer Interaction

Numerical Study on Wall Temperature Effects on Shock Wave/Turbulent Boundary-Layer Interaction

Investigation of Three-Dimensional Shock Wave/Turbulent-Boundary-Layer Interaction Initiated by a Single Fin

Two and Three Dimensional Numerical Simulation of Supersonic Ramped Inlet

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