Numerical investigation of supersonic flow breakdown at the inlet duct throttling

Gounko, Yu. P.; Mazhul, I. I.; Nurutdinov, V. I.

doi:10.1134/s0869864314020036

Cited by 14 publications

(3 citation statements)

References 2 publications

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“…Based on the oblique shock solution to the Rankine-Hugoniot equations, we obtain the cowl compression angle α 1 and the Mach number Ma cowl before the cowl-induced incident shock. Statistically speaking, α 1 is usually 10 • -15 • (Weir et al 1989;Rodi, Emami & Trexler 1996;Schmitz & Bissinger 1998;Sanders & Weir 1999;Taguchi et al 2003;Albertson, Emami & Trexler 2006;Sanders & Weir 2008;Chang et al 2012;Tan et al 2012;Gounko, Mazhul & Nurutdinov 2014;Zhang et al 2015Zhang et al , 2016You et al 2017;Zhang et al 2017;Devaraj et al 2020;Huang et al 2021;Saravanan et al 2021), as shown in figure 2.…”

Section: Description Of Simplified Inlet Modelmentioning

confidence: 99%

On incident shock wave/boundary layer interactions under the influence of expansion corner

Guo,

Tan,

Zhang

et al. 2024

J. Fluid Mech.

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Cowl-induced incident shock wave/boundary layer interactions (ISWBLIs) under the influence of shoulder expansion represent one of the dominant phenomena in supersonic inlets. To provide a more comprehensive understanding of how an expansion corner affects the ISWBLI, a detailed experimental and analytical study is performed in a Mach 2.73 flow in this work. Pressure measurement, schlieren photography and surface oil-flow visualisation are used to record flow features, including the pressure distribution, separation extent and surface-flow topological structures. Our results reveal three types of ISWBLIs influenced by the expansion corner. When the shock intensity is weak, the separation is small scale with the expansion waves emanating from the expansion corner. This is the first type of expansion-corner-affected ISWBLI (EC-ISWBLI). When the incident shock wave is strong, large-scale separation occurs, accompanied by the disappearance of expansion waves, forming the second type of EC-SWBLI. The expansion corner induces a ‘lock-in’ effect in which the separation onset is consistently locked near the expansion corner regardless of the incident shock intensity and impingement position. The third type of EC-ISWBLI occurs when the shock is sufficiently strong and the impingement point is close to the expansion corner. In this interaction, the ‘lock-in’ effect ceases to manifest. Moreover, a shock polar-incorporating inviscid model is employed to elucidate the shock patterns. Two criteria are established by combining free interaction theory with this model. The first criterion provides valuable insights into the evolution of separations with a minimal overall pressure rise and the second criterion determines the threshold for the occurrence of the ‘lock-in’ effect.

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Section: Description Of Simplified Inlet Modelmentioning

confidence: 99%

On incident shock wave/boundary layer interactions under the influence of expansion corner

Guo,

Tan,

Zhang

et al. 2024

J. Fluid Mech.

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“…It should be noted that the time needed for the development of such subroutines is appreciably shorter than the time necessary for the development of an in-house code with similar capabilities owing to a large number of builtin functions. The chosen software package is universal and is suitable for simulating incompressible [17] and compressible [18] flows. However, for solving specific problems of aeromechanics, such as, e.g., simulation of the laminar-turbulent transition [19], the use of research codes based on high-order schemes with low dissipation is preferable.…”

Section: Introductionmentioning

confidence: 99%

Development and testing of a numerical simulation method for thermally nonequilibrium dissociating flows in ANSYS Fluent

Shoev

Bondar

Oblapenko

et al. 2016

Thermophys. Aeromech.

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Various issues of numerical simulation of supersonic gas flows with allowance for thermochemical nonequilibrium on the basis of fluid dynamic equations in the two-temperature approximation are discussed. The computational tool for modeling flows with thermochemical nonequilibrium is the commercial software package ANSYS Fluent with an additional userdefined open-code module. A comparative analysis of results obtained by various models of vibration-dissociation coupling in binary gas mixtures of nitrogen and oxygen is performed. Results of numerical simulations are compared with available experimental data.

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“…That is why the critical condition of the nonuniform flow choking has to use for determination of the limiting cross-sectional area of the inlet throat in this case. Namely, the integral function (M) q was used which was introduced in the work [8] and which is, for the nonuniform flow, an analog of the reduced flow-rate function q(M) known for the one-dimensional flow:…”

Section: Regimes Of the Inlet Starting And Breakdown Of Supersonic Flmentioning

confidence: 99%

An investigation of starting processes and flow patterns occurring in hypersonic axisymmetric inlets of internal compression

Gounko

Mazhul

Kavun

2017

AIP Conference Proceedings

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Numerical investigation of supersonic flow breakdown at the inlet duct throttling

Cited by 14 publications

References 2 publications

On incident shock wave/boundary layer interactions under the influence of expansion corner

On incident shock wave/boundary layer interactions under the influence of expansion corner

Development and testing of a numerical simulation method for thermally nonequilibrium dissociating flows in ANSYS Fluent

An investigation of starting processes and flow patterns occurring in hypersonic axisymmetric inlets of internal compression

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