Numerical and experimental investigations of pseudo-shock systems in a planar nozzle: impact of bypass mass flow due to narrow gaps

Giglmaier, M.; Quaatz, Jan Frederik; Gawehn, Thomas; Gülhan, Ali; Adams, Nikolaus A.

doi:10.1007/s00193-013-0475-2

Cited by 14 publications

(4 citation statements)

References 33 publications

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“…At the beginning of the propagation, the fluctuation intensity is higher, and at the end, the intensity is lower. Such flow development has been reported by Kameli et al [31], Giglmaier et al [32], and Vignesh et al [35]. Also, Matsuo et al [34], Wang et al [35], and Xue et al [36] have carried out studies on the compressible flow in parallel-walled ducts and reported the presence of the shock train.…”

Section: Introductionsupporting

confidence: 61%

Numerical analysis of the shock train evolution in planar nozzles with throat length

Tolentino,

Mírez,

Caraballo

2023

FME Transactions

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In the present investigation, the behavior of compressible flow in planar nozzles with throat length is analyzed to determine the flow velocity range and pressure fluctuations in the throat section. The flow field was simulated in 2D computational domains with the ANSYS-Fluent R16.2 code. The RANS model was applied for steady-state flow. The governing equations used are the conservation of mass, momentum, energy, and the ideal gas equation of state. The Sutherland equation was used for the viscosity as a function of temperature. The Spalart-Allmaras turbulence model was used to model the flow turbulence, which was validated with experimental pressure data. In the throat section, for the central region of the flow, as the throat length increases, the flow fluctuates and decelerates. Oblique shock waves are produced, and a shock train region is formed. The flow velocity is transonic and is in the Mach number range of 1 to 1.2, and the static pressure is in the range of 0.37 to 0.52. Therefore, as a result of flow fluctuations, throat length has a significant effect on flow development.

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Section: Introductionsupporting

confidence: 61%

Numerical analysis of the shock train evolution in planar nozzles with throat length

Tolentino,

Mírez,

Caraballo

2023

FME Transactions

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“…standard k À ε model) generally has difficulties to be able to predict the length of separation accurately. With the introduced compressibility modifications, the modified k À ε model preforms much better and even shows advantages to the k À u SST turbulence model which is widely used for separation flow predictions [37,38].…”

Section: Main Flowmentioning

confidence: 96%

Effects of self-throttling on combustion enhancement in supersonic flow with transverse injection

Han

Chen

2015

International Journal of Hydrogen Energy

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“…Many of the past numerical works on shock trains used linear-eddy viscosity models and do not consider the three-dimensional flow. Numerical work by Giglmaier et al [5] is one of the few that show in detail the benefits of using RSM-based turbulence models for shock train simulations. Scale resolving methods such as LES [6,7] and WMLES [8] show promising results, however, the Reynolds number must often be reduced for the former, and the latter relies on near-wall modelling which may not be applicable in separated regions.…”

Section: Introductionmentioning

confidence: 99%

Numerical Simulations of Multiple Shock Wave Boundary Layer Interactions

Boychev

Barakos

Steijl

2021

AIAA Scitech 2021 Forum

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Shock wave boundary layer interactions occur in many aerospace applications, and of particular interest are the interactions occurring in high-speed intakes. The high-speed intakes aim to decelerate the flow with minimum losses using a series of oblique shocks followed by a weak normal shock. Depending on the state of the boundary layer and on the upstream Mach number, multiple shocks can form in the throat of the intake. Often, they are referred to as shock trains, or pseudo-shocks and can have a significant impact on the inake performance. The in-house CFD solver of the Unversity of Glasgow is used here, to investigate an isolated multiple shock interaction and quantify the effect of different non-linear turbulence models. The non-linear models, and their ability to account for the Reynolds stress anisotropy, resolve the corner flows and give favourable agreement with experiments. As a second step, shock train simulations in a geometry more representative of a high-speed intake are performed. Three different pitot intakes are considered and performance metrics based on the total pressure recovery and flow distortion are evaluated at different free-stream conditions. The predicted shock trains are highly asymmetric and the strong sensitivity of the total pressure recovery and flow distortion to the intake geometry is observed which reduces at higher incidence angles.

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Numerical and experimental investigations of pseudo-shock systems in a planar nozzle: impact of bypass mass flow due to narrow gaps

Cited by 14 publications

References 33 publications

Numerical analysis of the shock train evolution in planar nozzles with throat length

Numerical analysis of the shock train evolution in planar nozzles with throat length

Effects of self-throttling on combustion enhancement in supersonic flow with transverse injection

Numerical Simulations of Multiple Shock Wave Boundary Layer Interactions

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